1. AE 521 Design Report for the M-Jet Stratosphere
Michael B. Johnson
Instructor: Dr. Ron Barrett Department of Aerospace Engineering
GTA: Riley Sprunger December 16th, 2016

2. Aerospace Engineering Department ii
Table of Contents
Page #
List of Symbols.........................................................................................................................................................iv
Greek Symbols ......................................................................................................................................................iv
Subscripts ...............................................................................................................................................................v
Acronyms ...............................................................................................................................................................v
List of Tables .............................................................................................................................................................v
List of Figures............................................................................................................................................................6
Acknowledgments......................................................................................................................................................8
1 Introduction...................................................................................................................................................9
2 Mission Specifications and Profiles, Mission Profile and Descriptions of Similar Aircraft.......................10
2.1 Mission Specification and Profile, Mission Profile and Discussion.....................................................10
2.2 Descriptions of Similar Airplanes ........................................................................................................11
3 Mission Weight Estimates ..........................................................................................................................12
3.1 STAMPED Analysis and Data Base for Takeoff Weights and Empty Weights of Similar Airplanes .12
3.2 Determinations of Weight Trends Using STAMPED Data..................................................................12
3.3 Determination of Mission Weights.......................................................................................................13
3.4 Conclusions and Recommendations.....................................................................................................14
4 Performance Constraint Analysis................................................................................................................15
4.1 Stall Speed Constraints.........................................................................................................................15
4.2 Takeoff Distance Constraints ...............................................................................................................15
4.3 Landing Distance Constraints...............................................................................................................15
4.4 Drag Polar Estimation ..........................................................................................................................15
4.5 Climb Constraints.................................................................................................................................16
4.6 Maneuvering Constrains.......................................................................................................................17
4.7 Speed Constraints.................................................................................................................................17
4.8 Determination of Takeoff Wing Loading and Takeoff Thrust-to-Weight Ratio ..................................17
4.9 Conclusions and Recommendations.....................................................................................................19
5 Class I Configuration Matrix and Initial Downselection ............................................................................20
5.1 List of Items Which Have a Major Impact on the Design....................................................................20
5.2 Comparative Study of Airplanes with Similar Performance ................................................................20
5.3 Configuration Sweep and Selection .....................................................................................................20
5.4 Configuration Summary and Recommendation ...................................................................................22
6 Layout of the Cockpit and Fuselage............................................................................................................23
6.1 Layout Design of the Cockpit...............................................................................................................23
6.2 Layout of the Fuselage .........................................................................................................................24
6.3 Cockpit and Fuselage Summary and Recommendations......................................................................25
7 Layout Design of the Propulsion Installation..............................................................................................26
7.1 Selection and Layout of the Propulsion Installation.............................................................................26
7.2 Propulsion Summary and Recommendations.......................................................................................27
8 Class I Layout Design of the Wing.............................................................................................................28
8.1 Wing Design Layout ............................................................................................................................28
8.2 Wing Design Summary and Recommendations...................................................................................30
9 Class I Design of High Lift Devices ...........................................................................................................31
9.1 Design of High Lift Devices.................................................................................................................31
9.2 High Lift Devices Summary and Recommendations ...........................................................................32
10 Class I Design of Empennage.....................................................................................................................33
10.1 Empennage Design Procedures ............................................................................................................33
10.2 Empennage Design Conclusion and Recommendations ......................................................................34
11 Class I Design of the Landing Gear............................................................................................................35
11.1 Landing Gear Design Procedure ..........................................................................................................35
11.2 Landing Gear Conclusions and Recommendations..............................................................................37
12 Class I Weight and Balance Analysis .........................................................................................................38
12.1 Preliminary Three View .......................................................................................................................38
12.2 Class I Weights Breakdown .................................................................................................................40
12.3 Class I Weight and Balance Calculation ..............................................................................................40
12.4 Weight and Balance Conclusions and Recommendations....................................................................44
13 V-n Diagram ...............................................................................................................................................45

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13.1 V-n Calculations...................................................................................................................................45
13.2 Presentation of the V-n Diagram..........................................................................................................45
13.3 V-n Diagram Conclusions and Recommendations...............................................................................46
14 Class I Stability and Control Analysis ........................................................................................................47
14.1 Stability and Control Analysis..............................................................................................................47
14.2 Conclusions and Recommendations.....................................................................................................49
15 Class I Drag Polar and Performance Analysis ............................................................................................50
15.1 Drag Polar Analysis with Wetted Area Breakdown.............................................................................50
15.2 Conclusions and Recommendations.....................................................................................................51
16 Analysis of Weight and Balance, Stability and Control and L/D Results...................................................52
16.1 Impact of Weight and Balance and Stability and Control Results on the Design.................................52
16.2 Analysis of Critical L/D Results...........................................................................................................53
16.3 Design Iterations Performed.................................................................................................................53
16.4 Conclusions and Recommendations.....................................................................................................54
17 Preliminary Three View and Extra Credit Figures......................................................................................55
17.1 CAD Figures of Class I Aircraft...........................................................................................................55
17.2 Table of Class I Aircraft Characteristics ..............................................................................................55
17.3 Class I Aircraft Description..................................................................................................................55
17.4 Operation Concept Figures...................................................................................................................57
18 Description of Major Systems with Ghost Views.......................................................................................57
18.1 List of Major Systems ..........................................................................................................................61
18.2 Description of the Flight Control System.............................................................................................62
18.3 Description of the Fuel System ............................................................................................................65
18.4 Description of the Electrical System ....................................................................................................67
18.5 Description of the Hydraulic System....................................................................................................70
18.6 Description of the Environmental Control System...............................................................................72
18.7 Conflict Analysis..................................................................................................................................74
18.8 Major Systems Summary and Recommendations ................................................................................74
19 Sizing of the Landing Gear Tires and Struts using Class II Methods .........................................................75
19.1 Description of Major Landing Gear Components and Disposition ......................................................75
19.2 CAD Drawings of Landing Gear Components, Disposition and Integration into Airframe.................76
19.3 Conclusions and Recommendations.....................................................................................................78
20 Initial Structural Arrangement ....................................................................................................................79
20.1 Layout of Structural Components.........................................................................................................79
20.2 CAD Drawings of Structural Layout....................................................................................................79
20.3 Initial Structural Arrangement Summary and Recommendations........................................................82
21 Class II Weight and Balance.......................................................................................................................83
21.1 Class II Weight and Balance Calculations ...........................................................................................83
21.2 Class II CG Positions on the Airframe, CG Excursion.........................................................................84
21.3 Conclusions and Recommendations.....................................................................................................85
22 Class II Weight and Balance Analysis........................................................................................................86
22.1 Class II Weight and Balance Analysis .................................................................................................86
22.2 Conclusions and Recommendations.....................................................................................................87
23 Updated 3-View..........................................................................................................................................88
23.1 Updated 3-View ...................................................................................................................................88
23.2 Summary and Recommendations.........................................................................................................88
24 Advanced Technologies..............................................................................................................................90
25 Risk Mitigation ...........................................................................................................................................91
26 Manufacturing Plan.....................................................................................................................................92
26.1 Materials...............................................................................................................................................92
26.2 Assembly Method.................................................................................................................................92
27 Cost Analysis..............................................................................................................................................95
28 Marketing Plan and Finale..........................................................................................................................96

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List of Symbols
Symbol Description Units
a............................................................... Speed of Sound...........................................................................ft/s
b........................................................................Span ..................................................................................... ft
c.......................................................................Chord .................................................................................... ft
c’...................................................Wing Chord with Flaps Down ................................................................. ft
cj ............................................... Thrust Specific Fuel Consumption.....................................................lb/lb-hr
c̅ .........................................................Mean Geometric Chord ......................................................................in
CDo .................................................... Parasite Drag Coeffcient....................................................................n/a
CL......................................................Airplane Lift Coefficient ...................................................................n/a
Cl ......................................................Sectional Lift Coefficient...................................................................n/a
CLmax .............................................Max Airplane Lift Coefficient ...............................................................n/a
Clmax ............................................. Max Sectional Lift Coefficient...............................................................n/a
Cnβ......................................Yawing Moment due to Sideslip Coefficient....................................................n/a
df ............................................................Fuselage Diameter ..........................................................................in
e.............................................................Oswald Efficiency ........................................................................n/a
f ................................................................. Parasite Area..............................................................................ft2
i................................................................Incidence Angle .............................................................................°
kλ...................................................Taper Ratio Correction Factor ...............................................................n/a
KΛ ................................................Wing Sweep Correction Factor ..............................................................n/a
l....................................................................... Length....................................................................................in
lf...............................................................Fuselage Length............................................................................in
lfc.........................................................Fuselage Cone Length .......................................................................in
L/D ........................................................ Lift-to-Drag Ratio.........................................................................n/a
Mcr .......................................................Cruise Mach Number......................................................................n/a
Mff....................................................... Mission Fuel Fraction......................................................................n/a
N........................................................... Number of Engines........................................................................n/a
P...................................................................Static Load .............................................................................. lbf
q............................................................. Dynamic Pressure.........................................................................n/a
R ................................................................ Gas Constant..............................................................ft-lb/slug-°R
Rn...........................................................Reynold’s Number........................................................................n/a
S...................................................................Wing Area ...............................................................................ft2
Swet..............................................................Wetted Area ..............................................................................ft2
Swf......................................................... Flapped Wing Area.........................................................................ft2
t/c..................................................... Thickness-to-Chord Ratio...................................................................n/a
T .................................................................Temperature............................................................................. °R
T/W.................................................... Thrust-to-Weight Ratio.....................................................................n/a
Ude ............................................................. Vertical Gust.............................................................................ft/s
V......................................................................Speed ..................................................................................kts
V̅ ...........................................................Volume Coefficient .......................................................................n/a
W....................................................................Weight ...................................................................................lb
W/S........................................................... Wing Loading.........................................................................lb/ft2
Greek Symbols
Symbol Description Units
αδf................................... Angle of Attack Increase Due to Flap Deflection............................................... Rad
γ............................................................ Specific Heat Ratio........................................................................n/a
Γ................................................................Dihedral Angle..............................................................................°
δ..............................................................Deflection Angle ............................................................................°
∆ ...........................................................Incremental Change .......................................................................n/a
ε ..............................................................Downwash Angle............................................................................°
ηi ..........................................Inboard Location as Percent of Half Span ......................................................n/a
ηo ..........................................Outboard Location as Percent Half Span .......................................................n/a
θ.......................................................... Temperature Gradient......................................................................n/a
θfc.....................................................Max Fuselage Cone Angle.....................................................................°
λ.................................................................. Taper Ratio..............................................................................n/a
Λc/4................................................. Quarter Chord Sweep Angle....................................................................°
ρ.............................................................Density Parameter......................................................................lb/ft3
σ..............................................................Pressure Gradient.........................................................................n/a

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Subscripts
Symbol Description Units
App...................................................... Approach Parameter.......................................................................n/a
C ........................................................Cruise/Clean Parameter ....................................................................n/a
e..............................................................Empty Parameter .........................................................................n/a
e_tent..............................................Tentative Empty Parameter .................................................................n/a
F................................................................Fuel Parameter ...........................................................................n/a
Fused .................................................Mission Fuel Parameter ....................................................................n/a
h.......................................................Horizontal Tail Parameter...................................................................n/a
L ............................................................Landing Parameter........................................................................n/a
m..........................................................Main Gear Parameter ......................................................................n/a
n...........................................................Nose Gear Parameter ......................................................................n/a
oe_tent ....................................Tentative Operating Empty Parameter.........................................................n/a
Pl+Crew.........................................Payload and Crew Parameter ................................................................n/a
r ............................................................... Root Parameter...........................................................................n/a
t..................................................................Tip Parameter............................................................................n/a
TO..........................................................Takeoff Parameter ........................................................................n/a
v......................................................... Vertical Tail Parameter.....................................................................n/a
W.............................................................Wing Parameter ..........................................................................n/a
Acronyms
Symbol Description Units
AAA ...............................................Advanced Aircraft Analysis.................................................................n/a
AC ....................................................... Aerodynamic Center.......................................................................n/a
AIAA...........................American Institute of Aeronautics and Astronautics ..............................................n/a
ANSUR .................................... U.S. Army Anthropometry Survey............................................................n/a
AR ............................................................. Aspect Ratio.............................................................................n/a
CG ..........................................................Center of Gravity .........................................................................n/a
CGR......................................................... Climb Gradient...........................................................................n/a
EIS......................................................... Entry into Service.........................................................................n/a
FAR............................................... Federal Aviation Regulation.................................................................n/a
FS ............................................................Fuselage Station............................................................................in
GAMA.............................. General Aviation Manufacturers Association....................................................n/a
HSC.......................................................High Speed Cruise ........................................................................n/a
IFR.....................................................Instrument Flight Rules ....................................................................n/a
LBL .......................................................... Left Butt Line..............................................................................in
LRC...................................................... Long Range Cruise........................................................................n/a
MAC................................................Mean Aerodynamic Chord..................................................................n/a
NBAA................................... National Business Aviation Association........................................................n/a
PIC......................................................... Pilot in Command.........................................................................n/a
RBL......................................................... Right Butt Line.............................................................................in
RFP...................................................... Request for Proposal.......................................................................n/a
ROC...........................................................Rate of Climb.......................................................................... fpm
SM.............................................................Static Margin ............................................................................n/a
STAMPED ............Statistical Time and Market Predictive Engineering Design ........................................n/a
TSFC ........................................ Thrust Specific Fuel Consumption...................................................lbf/lbf-hr
WL...............................................................Water Line ................................................................................in
List of Tables
Page #
Table 2.2.1: Key Characteristics of Similar Aircraft ...................................................................................................11
Table 4.4.1: Drag Polar Results...................................................................................................................................16
Table 6.2.1: Fuselage Dimensions...............................................................................................................................24
Table 8.1.1: Key Aircraft Parameters ..........................................................................................................................28
Table 9.1.1: Various Lift Coefficients.........................................................................................................................31
Table 9.1.2: High Lift Device Sizing Results..............................................................................................................32
Table 9.1.3: High Lift Device Sizing Results..............................................................................................................32
Table 10.1.1: Empennage Salient Characteristics........................................................................................................33
Table 11.1.1: Landing Gear Salient Characteristics ....................................................................................................35

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List of Tables (cont)
Table 12.1.1: Center of Gravity Legend......................................................................................................................38
Table 12.1.1: Weights from Preliminary Sizing..........................................................................................................40
Table 12.2.2: Component Weight Breakdown ............................................................................................................40
Table 12.3.1: Maximum C.G. Excursions ...................................................................................................................41
Table 12.3.2: C.G. Excursion for Loading Case 1.......................................................................................................42
Table 12.3.3: Key Component Final C.G. Locations...................................................................................................42
Table 15.1.1: Drag Polar Results.................................................................................................................................50
Table 16.2.1: Weight Change due to L/D Sensitivity..................................................................................................53
Table 16.2.2: Class I L/D.............................................................................................................................................53
Table 17.2.1: Class I Salient Characteristics ...............................................................................................................55
Table 17.2.2: Class I Salient Characteristics ...............................................................................................................55
Table 18.2.1: Stratosphere’s Flight Controls...............................................................................................................62
Table 18.3.1: Fuel Pump and Line Sizing ...................................................................................................................65
Table 19.1.1: Selected Tire Specifications (Table 2.7 and 2.8 Ref. 44) ......................................................................75
Table 19.1.2: Maximum Landing Gear Loads.............................................................................................................75
Table 19.1.3: Strut Sizing Results ...............................................................................................................................75
Table 21.1.1: Class II Weights and C.G. Locations.....................................................................................................83
Table 23.1.1: M-Jet Stratosphere Salient Characteristics ............................................................................................88
Table 23.1.2: M-Jet Stratosphere Salient Characteristics ............................................................................................88
Table 23.2.1: Materials Breakdown.............................................................................................................................92
Table 26.27.1.1: Cost Estimation Results (From AAA)..............................................................................................95
List of Figures
Page #
Figure 2.1.1: Mission Profile.......................................................................................................................................10
Figure 2.2.5: CJ3+ Taxiing (Ref. 4) ............................................................................................................................11
Figure 2.2.5: Phenom 300 After Delivery (Ref. 9)......................................................................................................11
Figure 2.2.5: Learjet 75 Taxiing (Ref. 11)...................................................................................................................11
Figure 2.2.5: Falcon 2000S in Flight (Ref. 13)............................................................................................................11
Figure 2.2.5: CJ4 on the Ramp (Ref. 6).......................................................................................................................11
Figure 3.2.1: WE/WTO STAMPED Analysis Results...................................................................................................12
Figure 3.2.2: AR STAMPED Analysis Results...........................................................................................................13
Figure 4.8.1: Complete M-Jet Stratosphere Sizing Chart with STAMPED Vector.....................................................18
Figure 5.3.1: Concept of Operations for the M-Jet Stratosphere.................................................................................20
Figure 5.3.2: Nine Discarded Configurations..............................................................................................................21
Figure 5.3.3: Three Most Suitable Configurations ......................................................................................................22
Figure 6.1.1: Cockpit Side View (Scale 1:30).............................................................................................................23
Figure 6.1.2: Cockpit Top View (Scale 1:30)..............................................................................................................23
Figure 6.1.3: Cockpit Front View (Scale 1:30)............................................................................................................23
Figure 6.1.4: PIC Visibility Chart (Ref........................................................................................................................23
Figure 6.1.5: Cockpit Isometric Views (No Scale)......................................................................................................24
Figure 6.2.1: Fuselage Dimension (Scale 1:100).........................................................................................................24
Figure 6.2.2: Fuselage Side View (Scale 1:100)..........................................................................................................24
Figure 6.2.3: Fuselage Top View (Scale 1:30) ............................................................................................................24
Figure 6.2.4: Fuselage Front View (Scale 1:30)..........................................................................................................24
Figure 6.2.5: Cabin Side View, with Section Labels (Scale 1:80)...............................................................................25
Figure 6.2.6: Cabin Top View, with Passenger Labels (Scale 1:80) ...........................................................................25
Figure 6.2.7: Fuselage Isometric View (No Scale)......................................................................................................25
Figure 6.2.8: Cabin Cross Section (Scale 1:30)...........................................................................................................25
Figure 7.1.1: Mach vs. Altitude Chart for Various Engine Types (Fig. 5.1, p. 124, Ref. 19)......................................26
Figure 7.1.2: Engine Front View (Scale 1:10).............................................................................................................27
Figure 7.1.3: Engine Top View (Scale 1:20)...............................................................................................................27
Figure 7.1.4: Engine Side View (Scale 1:16) ..............................................................................................................27
Figure 7.1.5: Engine Isometric View (No Scale).........................................................................................................27
Figure 8.1.1: NASA SC(2)-0712 Airfoil Profile (Ref. 29) ..........................................................................................28
Figure 8.1.2: Half Span with Exposed Fuel Tank and Spar Lines (Scale 1:40)...........................................................29
Figure 8.1.3: Wing Top View (Scale 1:50) .................................................................................................................29

7. Aerospace Engineering Department 7
List of Figures (cont)
Figure 8.1.4: Wing Isometric Views (No Scale)..........................................................................................................30
Figure 8.1.5: Wing Side View (Scale 1:20).................................................................................................................30
Figure 9.1.1: Fully Aft Translating Fowler Flap (No Scale) .......................................................................................31
Figure 9.1.2: Wing Top View with High Lift Device Dimensions (Scale 1:100) .......................................................32
Figure 10.1.1: Horizontal Tail Side View (Scale 1:20) ...............................................................................................33
Figure 10.1.2: Horizontal Tail Top View (Scale 1:25)................................................................................................33
Figure 10.1.3: Horizontal Tail Front View (Scale 1:25)..............................................................................................33
Figure 10.1.4: Vertical Tail Top View (Scale 1:20) ....................................................................................................34
Figure 10.1.5: Vertical Tail Side View (Scale 1:25)....................................................................................................34
Figure 10.1.6: Vertical Tail Front View .....................................................................................................................34
Figure 10.1.7: Empennage Isometric View (No Scale) ...............................................................................................34
Figure 11.1.1: Landing Gear Front View (Scale 1:100) ..............................................................................................35
Figure 11.1.2: Landing Gear Side View (Scale 1:100)................................................................................................35
Figure 11.1.3: Landing Gear Top View (Scale 1:200) ................................................................................................36
Figure 11.1.4: Landing Gear Isometric View (No Scale)............................................................................................36
Figure 11.1.5: Main Gear Retracted (No Scale) ..........................................................................................................36
Figure 11.1.6: Nose Gear Retracted (No Scale) ..........................................................................................................36
Figure 11.1.7: Nose and Empennage Fuel Tanks (No Scale) ......................................................................................37
Figure 12.1.1: Preliminary Three View – Side (Scale 1:40)........................................................................................38
Figure 12.1.2: Preliminary Three View – Front (Scale 1:40) ......................................................................................38
Figure 12.1.3: Preliminary Three View – Top (Scale 1:40) ........................................................................................39
Figure 12.3.1: Center of Gravity Excursion Diagram..................................................................................................41
Figure 12.3.2: Preliminary Stratosphere Three View (Scale 1:64) and Isometric View (No Scale)............................43
Figure 13.2.1: Maneuver V-n Diagram .......................................................................................................................45
Figure 13.2.2: Gust V-n Diagram................................................................................................................................46
Figure 14.1.1: Longitudinal X-Plot..............................................................................................................................47
Figure 14.1.2: Multhopp Integration Used in Tail Sizing (Scale 1:125)......................................................................48
Figure 14.1.3: Lateral Projected Area for Cnβwf ..........................................................................................................49
Figure 14.1.4: Directional X-Plot ................................................................................................................................49
Figure 15.1.1: Stratosphere Perimeter Plot..................................................................................................................50
Figure 15.1.2: Class I Drag Polar Chart.......................................................................................................................51
Figure 16.1.1: New Center of Gravity Excursion Diagram (Post S&C Analysis).......................................................52
Figure 17.3.1: Class I Three View (Scale 1:64) and Isometric View (No Scale) ........................................................56
Figure 17.4.1: Stratosphere Before and During Takeoff (Ref. 37) ..............................................................................57
Figure 17.4.2: Stratosphere Flying Past Owner’s Lamborghini (Ref. 38) ...................................................................58
Figure 17.4.3: Stratosphere Flying Over the Flint Hills of Kansas (Ref. 39) ..............................................................58
Figure 17.4.5: Stratosphere Over New York City (Ref. 41)........................................................................................59
Figure 17.4.4: Stratosphere Flying Over the University of Kansas Campus (Ref. 40)................................................59
Figure 17.4.6: Stratosphere in Flight with F22s (Ref. 42) ...........................................................................................60
Figure 17.4.7: Stratosphere in Formation with F35s (Ref. 43)....................................................................................60
Figure 18.1.1: Overall System Isometric View (No Scale) .........................................................................................61
Figure 18.1.2: Overall System Front View (Scale 1:80)..............................................................................................61
Figure 18.1.3: Overall Systems Top View (Scale 1:80) ..............................................................................................62
Figure 18.2.1: Flight Control System Multi-Isometric View (No Scale).....................................................................63
Figure 18.2.2: Flight Control System Three View (Scale 1:100) ................................................................................64
Figure 18.3.1: Fuel System Isometric View (No Scale) ..............................................................................................65
Figure 18.3.2: Fuel System Detail View (No Scale)....................................................................................................66
Figure 18.3.3: Fuel System Front View (Scale 1:100) ................................................................................................66
Figure 18.3.4: Fuel System Top and Side View (Scale 1:100)....................................................................................67
Figure 18.4.1: Electrical Load Profile for Stratosphere...............................................................................................68
Figure 18.4.2: Electrical System Isometric View (No Scale)......................................................................................68
Figure 18.4.3: Electrical System Three View (Scale 1:100)........................................................................................69
Figure 18.4.4: Electrical System Detail Isometric View (No Scale) ...........................................................................70
Figure 18.5.1: Hydraulic System Detailed View (No Scale).......................................................................................70
Figure 18.5.2: Hydraulic System Isometric View (No Scale) .....................................................................................70
Figure 18.5.3: Hydraulic System Three View (Scale 1:100).......................................................................................71
Figure 18.6.1: Environmental System Detail Isometric View (No Scale)...................................................................72

8. Aerospace Engineering Department 8
List of Figures (cont)
Figure 18.6.2: Environmental System Isometric View (No Scale)..............................................................................72
Figure 18.6.3: Environmental Systems Three View (Scale 1:100)..............................................................................73
Figure 19.2.1: Landing Gear Front View (Scale 1:80) ................................................................................................76
Figure 19.2.2: Landing Gear Side View (Scale 1:80)..................................................................................................76
Figure 19.2.3: Landing Gear Top View (Scale 1:80) ..................................................................................................77
Figure 19.2.4: Nose Gear Retraction Isometric View (No Scale)................................................................................77
Figure 19.2.5: Main Gear Retraction and Fairing Multi-View (No Scale)..................................................................78
Figure 20.2.1: Structural Arrangement Front View (Scale 1:80).................................................................................80
Figure 20.2.2: Structural Arrangement Top View (Scale 1:80)...................................................................................80
Figure 20.2.3: Structural Arrangement Isometric View (No Scale) ............................................................................81
Figure 20.2.4: Structural Arrangement Side View (Scale 1:80) ..................................................................................81
Figure 21.2.1: Top View (Scale 1:80) with C.G. Locations ........................................................................................84
Figure 21.2.2: Side View (Scale 1:80) with C.G. Locations .......................................................................................85
Figure 21.2.3: Front View (Scale 1:80) with C.G. Locations......................................................................................85
Figure 22.1.1: Updated C.G. Excursion Diagram........................................................................................................86
Figure 23.2.1: M-Jet Stratosphere Three View (Scale 1:80) and Isometric View (No Scale).....................................89
Figure 26.2.1: Exploded View of the Stratosphere (No Scale)....................................................................................92
Figure 26.2.2: Manufacturing Facility Top View........................................................................................................93
Figure 26.2.3: Production Flow Chart .........................................................................................................................94
Figure 28.1.26.2.1: Payload Range Diagram...............................................................................................................96
Acknowledgments
The author would like to thank his girlfriend, Jacquelyn, for much support during AE 521, Kevin Johnson and
Ben Appel for editing help, his close friend, Roy, for many creative inspirations, and his drug of choice: caffeine. The
author has also included the following Haiku of praise:
Hail be to Roskam
And His design procedures
Hallowed be His name
The author would also like to thank his cat, Sammi, for editing his report. Sammi can be seen editing his report
in the following picture. The author requests that the grader not ding him for extra “fluff”.
The author would like to acknowledge Boulevard Brewing Co. for continued motivation and liquid
inspiration for helping him excel in AE 521. In fact, Boulevard is helping the author celebrate the end right now.

9. Aerospace Engineering Department 9
1 Introduction
This report outlines the design procedures and findings working toward a submission in the AIAA 2016-2017
Graduate Team Aircraft Design Competition. The Request for Proposal (RFP) is located on AIAA’s website. The RFP
outlines specifications for a six passenger and eight passenger variant; however, this report focuses on the eight
passenger version. This report contains the mission specification and mission profile, a study of similar aircraft,
preliminary weight sizing, preliminary performance sizing, configuration selection, cockpit and fuselage design,
engine selection and installation, Class I wing design, Class I high lift device sizing, Class I empennage design, Class
I landing gear design, Class I weight and balance analysis, maneuver and gust V-n diagrams, Class I stability and
control, Class I drag polar, analysis of Class I results, preliminary three view with salient characteristics, description
of major systems, Class II landing gear sizing, initial structural arrangement, Class II weight and balance calculations
and analysis, updated three view, advanced technology summary, risk mitigation, manufacturing plan, cost analysis,
and marketing plan.
The author has chosen a slightly aggressive design philosophy for the M-Jet Stratosphere. This means the
Stratosphere will be lighter weight, have a higher wing loading, and higher thrust-to-weight ratio than the predicted
2022 STAMPED Market Average. This slightly aggressive philosophy will apply to all design decisions.
Place Video Here

10. Aerospace Engineering Department 10
2 Mission Specifications and Profiles, Mission Profile and Descriptions of Similar Aircraft
The purpose of this chapter is to outline the mission specifications and mission profile defined by the RFP,
Ref. 1, as well as to showcase similar airplanes to define the market this design is entering by using the procedures
outlined in Ref. 2.
2.1 Mission Specification and Profile, Mission Profile and Discussion
The mission specifications are shown below (Ref. 1, p. 5). The RFP does not define long range cruise altitude
or speed; therefore, the author has selected Mach 0.80 at 45000 ft to achieve more efficient cruise characteristics when
compared to 35000 ft.
 FAR Part 25 Airworthiness
 2022 Entry into Service (EIS)
 High Speed Cruise (HSC): Mach 0.85 at 35000 ft
 Long Range Cruise (LRC): 2500 nm at Mach 0.80 and 45000 ft (with NBAA IFR Range with 100
nm alternate)
 Rate of Climb (ROC): 3500 fpm
 Service Ceiling: 45000 ft
 Maximum Sea Level Balanced Field Length (BFL): 4000 ft
 Maximum Sea Level Landing Field Length: 3600 ft
 Passengers: 8
 Baggage Capacity: 1000 lbs, 60 ft3
The mission profile can be seen in Figure 2.1.1, and was extracted from the above requirements. It lists LRC
because LRC yields the heaviest airplane.
Figure 2.1.1: Mission Profile

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2.2 Descriptions of Similar Airplanes
Table 2.2.1 displays key characteristics of each similar aircraft. First is the Cessna Citation CJ3+, and Figure
2.2.1 shows the aircraft. This aircraft is similar because of its passenger capabilities, range, and weight. Second is the
Cessna Citation CJ4, and Figure 2.2.2 shows the University of Kansas’s CJ4. The CJ4 is similar because of its range
and passenger requirements. Third is the Embraer Phenom 300, and Figure 2.2.3 shows the aircraft. The Phenom 300
is similar because of its passenger requirement and is a good baseline jet since it has succeeded in the market. Fourth
is the Bombardier Learjet 75, and Figure 2.2.4 shows the aircraft. The Learjet 75 is similar due to its range and
passenger capabilities. Finally, the Dassault Falcon 2000S, and Figure 2.2.5 shows the aircraft. The Falcon 2000S is
similar because of its passenger requirement and its high range capability. For further discussion on these airplanes,
see Chapter 5.3.2.2.
Table 2.2.1: Key Characteristics of Similar Aircraft
CJ3+ (Ref. 4) CJ4 (Ref. 5) Phenom 300 (Ref. 8) Learjet 75 (Ref. 8 Falcon 2000S (Ref. 8)
MTOW (lbs) 13870 17110 18999 21500 41000
Useful Load (lbs) 5560 6950 17968 7860 16450
Empty Weight (lbs) 8540 10280 11583 13890 24750
Max Range (nm) 2040 2165 1951 2040 3540
Max Speed (kts) 416 451 453 465 482
Service Ceiling (ft) 45000 45000 45000 51000 47000
Passengers (~) 9 10 8 9 10
EIS (yr) 2014 2010 2009 2013 2013
Sales Numbers (~) 33 (Ref. 3) 205 (Ref. 3) 257 (Ref. 7) 83 (Ref. 10) 25 (Ref. 12)
Figure 2.2.5: CJ3+ Taxiing (Ref. 4) Figure 2.2.5: Phenom 300 After
Delivery (Ref. 9)
Figure 2.2.5: Learjet 75 Taxiing (Ref. 11) Figure 2.2.5: Falcon 2000S in Flight (Ref. 13)
Figure 2.2.5: CJ4 on the Ramp
(Ref. 6)

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3 Mission Weight Estimates
The purpose of this chapter is to layout the Statistical Time and Market Predictive Engineering Design
(STAMPED) analysis techniques from p.71-79 in Ref. 2, and to show the results of the STAMPED analysis for
WE/WTO and aspect ratio (AR). STAMPED analysis provides market predictions based on time and also weights the
data on how successful each design was in the market, which allows for more accurate market predictions (Ref. 14).
This chapter also outlines the process of determining mission weights and the calculated mission weights for the M-
Jet Stratosphere.
3.1 STAMPED Analysis and Data Base for Takeoff Weights and Empty Weights of Similar Airplanes
A complete STAMPED analysis was performed for WE/WTO, and AR. The method comes directly from p.71-
79 in Ref. 2, and the data can be seen in this spreadsheet. Between 1963 and 2015, 46 business jets were used as data
points. Delivery numbers come from GAMA’s shipment database, while all other aircraft data comes from various
Janes’s All the World’s Aircraft, and Ref. 8. The spreadsheet contains specific references.
3.2 Determinations of Weight Trends Using STAMPED Data
After creating STAMPED data from 1963-2015, the author decided to exclude data from pre-1996. This
decision allows for an accurate trend to be established, as there was considerable change to the direction of the market
in 1996. This change is likely the result of many factors, including different design methods, new materials, or more
efficient engines. This
data can be found in this
spreadsheet on sheets 3-
9. Figure 3.2.1 shows
the results from the
WE/WTO STAMPED
analysis. The trends
show a decreasing
WE/WTO with a market
average of 0.560 by
2022, with a standard
Figure 3.2.1: WE/WTO STAMPED Analysis Results

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deviation of +/-
0.070. Using a
slightly aggressive
design philosophy
(lower weight), but
also taking into
account the large
fuel weight, the
author selected
WE/WTO of 0.591.
Figure 3.2.2
shows the STAMPED analysis results for AR. The same methods as the WE/WTO were followed from Ref. 2. The data
in Figure 3.2.2 can be found on sheet 10 in this spreadsheet. The trend lines seen in Figure 3.2.2 have poor R2
values,
but seem to follow the trends of the market. The projected 2022 market average AR was found to be 8.65, with a
standard deviation of +/- 0.25. Using a slightly aggressive design philosophy (more efficient wings) the author selected
an AR of 8.8.
3.3 Determination of Mission Weights
The methods outlined on p.53-80 in Ref. 2 were used to determine mission weights. Crew, personnel, and
baggage weights are defined in the RFP (Ref. 1), and were found to be 1556 lbs using a single pilot and four passengers
for LRC. The hand calculation can be found here. An initial WTO guess was selected as 14000lbs, based on current
business jets. L/D was selected to be 12, based on suggestions in Ref. 15. Thrust specific fuel consumption (TSFC)
was selected to be 0.65 lbf/lff-hr based on data from Ref. 16. Weight fractions were found using methods from p. 62-
68 in Ref. 2, and the Breguet Range and Endurance Equations in Ref. 2. Final weight fractions can be seen in Chapter
3.4.1. Sample hand calculations for the weight fractions, overall mission fuel fractions, and total fuel used can be
found here. A tentative operating empty weight, WOE_tent, and tentative standard empty weight, WE_tent , were found
using methods from p.70 in Ref. 2. Trapped fuel and oil, Wtfo was assumed to be 2% of WTO (Ref. 15, p. 7). WE was
found using WE/WTO selected from STAMPED data of 0.530. WTO_guess was then iterated until WE and WE_tent were
Figure 3.2.2: AR STAMPED Analysis Results

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within 0.5% of each other. WTO was found to be 13900 lbs, and can be seen in Chapter 3.4.1 with fuel weights, crew
and passenger weights, as well as all empty weights and trapped fuel and oil weights.
Advanced Aircraft Analysis (AAA) was used to verify these methods and calculations. Screenshots of AAA
outputs and graphs that verify those values below can be seen here. AAA values vary slightly since traditional
regression trends were used to predict weight values instead of STAMPED data. The sensitivity of takeoff weight with
respect to lift-to-drag ratio was also calculated and found to be -4012 lbs. Hand calculations for this sensitivity can be
found here.
3.4 Conclusions and Recommendations
3.4.1 Conclusions
The author concludes that:
 AAA confirms the conclusions in
Table 3.3.1 and Table 3.3.2
 Design WE/WTO = 0.591
 Design AR = 8.8
 Design Takeoff Weight = 13900 lbs
 Design Empty Weight = 8215 lbs
 Weight Fuel Used (LRC) = 4065 lbs
 Weight Fuel Reserves = 795 lbs
 W1/WTO = 0.99
 W2/W1 = 0.995
 W3/W2 = 0.995
 W4/W3 = 0.98
 W5/W4 = 0.74
 W6/W5 = 1
 W7/W6 = 0.99
 W8/W7 = 0.992
 W8/WTO = 0.70
 MFF_ResRange = 0.982
 MFF_ResLoiter = 0.960
 MFF_ResTotal = 0.943
 WTO = 13900 lbs
 WE = 7367 lbs
 Wpl+crew = 1556 lbs
 WF_used = 4065 lbs
 WF_Res = 795 lbs
 WTFO = 27.8 lbs
 ∂WTO/∂(L/D) = -4012 lbs
3.4.2 Recommendations
The author recommends that:
 STAMPED analysis not be used on AR trends since they tend to vary more by manufacturer than with
time.

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4 Performance Constraint Analysis
The purpose of this chapter is to outline the performance constraints given in the RFP (Ref. 1), and FAR 25
requirements, following procedures from p.102-160 of Ref. 2. This chapter also outlines the STAMPED analysis of
thrust-to-weight and wing loading that will help select the design point. Additionally, it shows the complete sizing
chart for the M-Jet Stratosphere, complete with overlaid STAMPED vectors.
4.1 Stall Speed Constraints
Since the RFP (Ref. 1) calls for a FAR Part 25 aircraft, there are no stall speed constraints (Ref. 18).
4.2 Takeoff Distance Constraints
The RFP requires a maximum balanced field length of 4000 ft at sea level standard conditions. For given values
of wing loading, the thrust-to-weight requirements were calculated to meet this requirement at three different CLmaxTO
conditions by following methods outlined on p.105-106 in Ref. 2. The three CLmaxTO values are 1.8, 2.0, and 2.2, which
come from Table 3.1 in Ref. 15. A sample hand calculation can be seen here, and a sizing chart with only takeoff
distance constraints can be seen here.
4.3 Landing Distance Constraints
The RFP requires a maximum landing field length of 3600 ft at sea level standard conditions. Four different
CLmaxL values were used to find required wing loadings, and were calculated following methods outlined on p. 118-
120 in Ref. 2. The four CLmaxL values are 2.4, 2.6, 2.8, and 3, and were selected from Table 3.1 in Ref. 2. A landing
weight to takeoff weight ratio, WL/WTO, was selected as 0.96 from Table 3.3 on p. 107 in Ref. 15. Approach speed,
Vapp, was found to be 109.5 kts, stall speed, Vstall, was found to be 84.27 kts, and required wing loading was calculated
using methods from p. 120 in Ref. 2. A sample hand calculation can be seen here, and a sizing chart with only landing
distance constraints can be seen here.
4.4 Drag Polar Estimation
To calculate the drag polar for various configurations, methods from p. 125-128 in Ref. 2 were followed. The
initial wetted area was found to be 1240 ft2
(Ref. 15, p. 124, Figure 3.22c). Cf was estimated to be 0.003, and the
parasite area was found to be 3.5 ft2
. To find CDo, an initial wing area of 232 ft2
was used based off an initial wing
loading guess of 60 psf. After completion of the STAMPED analysis for wing loading, CDo was recalculated and found

16. Aerospace Engineering Department 16
to be 0.0171 using the selected wing loading of 68 psf, which yields a wing area of 204 ft2
. Using the selected design
AR, in addition with CLmaxTO, CLmaxL, and CLmax that were selected to follow this authors design philosophy, CD was
calculated. Since CLmax values are only slightly aggressive, the flaps will be single Fowler flaps which create a low
∆CDo. Table 4.4.1 shows complete drag polar results, and selected parameters. Sample hand calculations can be found
here.
Table 4.4.1: Drag Polar Results
4.5 Climb Constraints
Since the M-Jet Stratosphere will obtain FAR Part 25 certification, there are six climb requirements already
defined. Additionally, the RFP (Ref. 1) gives a ROC of 3500 fpm. Definitions of the six FAR 25 climb requirements
were taken from page 144 of Ref. 15. Then, following methods from p. 141 Ref. 2, thrust-to-weight requirements were
calculated for the FAR 25 requirements. Sample hand calculations can be seen here, and a sizing chart with only FAR
25 climb constraints can be seen here.
To find the thrust-to-weight required to meet the 3500 fpm climb and the 45000 ft service ceiling, methods
from p.141 in Ref. 2 were followed. The 3500 fpm climb requirement was assumed to be valid to 20000 ft. For the
service ceiling, a 500 fpm requirement was used to meet FAR requirements (Ref. 15, p. 153). The required thrust-to-
weight found was then corrected for altitude. Sample hand calculations can be seen here, and a sizing chart with only
defined climb constraints can be seen here.
CDo (~) 0.0171
∆CDo Clean (~) 0
e Clean (~) 0.83
∆CDo TO Flaps (~) 0.013
e TO Flaps (~) 0.78
∆CDo Landing Flaps (~) 0.06
e Landing Flaps (~) 0.73
∆CDo Gear (~) 0.015
CLmax (~) 1.4
CLmaxTO (~) 2
CLmaxL (~) 2.8
CD Clean (~) 0.103
CD TO Gear Up (~) 0.216
CD TO Gear Down (~) 0.231
CD Landing Gear Up (~) 0.466
CD Landing Gear Down (~) 0.481
CD Approach Gear Down (~) 0.354

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4.6 Maneuvering Constrains
Since the only maneuvering constraints given by the RFP (Ref. 1) are cruise conditions (1 g maneuvers),
maneuvering and speed constraints will be treated as one. See Chapter 4.7 for speed constraints.
4.7 Speed Constraints
Two speed constraints are applied to this sizing chart: high speed cruise (HSC), and long range cruise (LRC).
HSC is defined as Mach 0.85 at 35000 ft, and LRC is defined as Mach 0.80 at 45000 ft. Since both conditions are at
transonic Mach numbers, compressibility drag was accounted for. At HSC ∆CDo is 0.01, and at LRC ∆CDo is 0.003
(Figure 3.32, p. 166, Ref. 15). For a given set of wing loadings, thrust-to-weight ratios were found using methods from
p. 157 in Ref. 2. Since these were calculated at altitude, they were corrected to sea level values. Sample hand
calculations can be seen here, and a sizing chart with only speed constraints can be seen here.
4.8 Determination of Takeoff Wing Loading and Takeoff Thrust-to-Weight Ratio
Wing loading and the thrust-to-weight ratio were determined based off of the constraints outlined in Chapters
4.1-4.7, and a STAMPED analysis of wing loading and thrust-to-weight ratio. A STAMPED analysis following
methods outlined in Ref. 2 was used to determine market trends and to predict the market design point for 2022. The
complete STAMPED analysis can be seen in this spreadsheet on sheets 11, 12, and 13. For determination of wing
loading and thrust-to-weight ratio, STAMPED data before 1996 was disregarded for the same reason mentioned in
Chapter 3.2. The thrust-to-weight STAMPED graph with market predictions can be seen here, and the wing loading
STAMPED analysis graph with market can be seen here. The STAMPED vector of thrust-to-weight versus wing
loading was overlaid on the design constraint requirements sizing chart. The complete sizing chart can be seen in
Figure 4.8.1. The STAMPED vector is broken in ten year increments, with the beginning year labeled. The 2022
STAMPED prediction is labeled on the sizing chart, and the dotted blue box shows +/- one standard deviation from
2022. Then, using the 2022 market prediction, a design point was selected on the sizing chart. The design point was
selected to be slightly aggressive, hence the thrust-to-weight ratio and wing loading are higher than the 2022 market
prediction. The thrust-to-weight ratio was selected to be 0.39 and the wing loading was selected to be 68 psf. From
these two values wing area and thrust can be calculated. See Chapter 4.9.1 for a complete design point breakdown.
AAA was used to verify the sizing chart created using methods from Ref. 2. Complete outputs and graphs can
be seen here. AAA values are slightly different than values found using methods from Ref. 2, since it did not use
STAMPED data.

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Figure 4.8.1: Complete M-Jet Stratosphere Sizing Chart with STAMPED Vector

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4.9 Conclusions and Recommendations
4.9.1 Conclusions
The author concludes that:
 Design Max Takeoff Weight = 13900 lbs
 Design Thrust-to-Weight ratio = 0.39
 Design Thrust = 5421 lbs
 Design Wing Loading = 68 psf
 Design Wing Area = 204 ft2
 Design AR = 8.8
 Initial Wetted Area = 1240 ft2
 Design CLmaxTO = 2
 Design CLmaxL = 2.8
 Design CLmaxClean = 1.4
 Design CDo = 0.0171
 ∆CDo Clean = 0
 e Clean = 0.83
 ∆CDo TO Flaps = 0.013
 e TO Flaps = 0.78
 ∆CDo Landing Flaps = 0.06
 e Landing Flaps = 0.73
 ∆CDo Gear = 0.015
 CD Clean = 0.103
 CD TO Gear Up = 0.216
 CD TO Gear Down = 0.231
 CD Landing Gear Up = 0.466
 CD Landing Gear Down = 0.481
 CD Approach Gear Down = 0.354
 AAA confirms sizing constraints and rough
design point found using STAMPED
methods
4.9.2 Recommendations
The author recommends that:
 A higher fidelity model for weight and performance sizing be used.
 STAMPED analysis be limited to the past 20 years to increase prediction accuracy.

20. Aerospace Engineering Department 20
Figure 5.3.1: Concept of Operations for the M-Jet Stratosphere
5 Class I Configuration Matrix and Initial Downselection
The purpose of this chapter is to determine the configuration of the M-Jet Stratosphere by considering items that
have a large impact on the design and by studying airplanes with similar performance. This chapter presents 12
different configurations, with explanations why each were chosen or discarded. Configuration selection follows
procedures from p. 11-12, 102 of Ref. 19.
5.1 List of Items Which Have a Major Impact on the Design
The RFP (Ref. 1) outlines specific mission specifications that have major impact on the design of the M-Jet
Stratosphere. Those specifications include the following:
 FAR Part 25 Certification
 HSC of Mach 0.85 at 35000 ft
 ROC of 3500 fpm
 Service ceiling of 45000 ft
 Maximum takeoff balanced field
length of 4000 ft
 Maximum landing field length of
3600 ft
 LRC of 2500nm with four passengers
 Eight passenger capability
 1000 lbs/60 ft3
of baggage
Additionally, the author has selected to perform LRC missions at 45000 ft and Mach 0.80 to achieve more
efficient performance characteristics.
5.2 Comparative Study of Airplanes with Similar Performance
Chapter 2.2 presents five business jets with similar performance. Their sales numbers and key characteristics
are displayed in Chapter 2.2, as well as how they are similar. For a more in-depth discussion of these airplanes, see
Chapter 5.3.2.2.
5.3 Configuration Sweep and Selection
5.3.1 Concept of Operations
The M-Jet Stratosphere will be operated similarly to other light business jets. The target customer is a
company that requires frequent transport to cities within 2500 nm of their location. A typical operation will include
loading of passengers and their baggage, taxi and takeoff, cruise to destination, landing and taxiing, and finally
unloading of passengers and baggage. Figure 5.3.1 shows the concept of operations chart.

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5.3.2 Selection of the Overall Configuration
5.3.2.1 Aircraft Category
The M-Jet Stratosphere falls into the business jet category, as defined by Ref. 19 on p. 47.
5.3.2.2 Discussion of Similar Aircraft
The M-Jet Stratosphere will enter the light business jet market where it will have many competitors. Chapter
2.2 outlines five similar aircraft including sales numbers and key characteristics. These five aircraft all have a very
similar configuration. This configuration has been accepted by the market and has proven successful. Each aircraft’s
interior varies by manufacturer, but the light business jet market has accepted a club seat design. A club is composed
of four seats, two facing forward and two facing aft. Three views and floorplans for all five jets can be seen here. The
CJ3+ has performed well in the light business jet market and is known as a fast and comfortable light jet. The CJ4 has
been successful with sales, although it is considered too big for a light jet but not big enough for a midsize (Ref. 22).
The Phenom 300 has had successful sales and is known for giving large jet styling and comfort to a light jet (Ref. 23).
The Learjet 75 is much pricier than most light jets, but provides more cabin length as it tries to lure midsize jet
customers. It maintains loyal Learjet customers, but many in industry feel it falls short of where it should be for the
price (Ref. 24). The Falcon 2000S is an expensive jet for its passenger capacity, as it manages to span the midsize jet
market with large light jet passenger capabilities (Ref. 25).
5.3.2.3 Configuration Sweep of Possible Candidates
Twelve different configurations were designed and considered as possible candidates for the M-Jet
Stratosphere. From those twelve, three
were deemed most suitable and nine
were discarded. Figure 5.3.1 shows all
nine discarded configurations.
Configuration 1 has wing tip fuel tanks
and was discarded because that design is
outdated. Configuration 2 has wing
mounted engines and was discarded
because a rotor non-containment event
would puncture the pressure vessel.
Configuration 3 has a V-tail and was Figure 5.3.2: Nine Discarded Configurations

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discarded because it causes higher stresses on the fuselage and also requires more complex and costly control system.
Configuration 4 has a twin boom tail and was discarded due to increased structural weight concerns. Configuration 5
has a low canard, high main wing, and wing mounted engines, and was discarded because it will be difficult to trim.
Configurations 6, 7, 8, and 9 were discarded because they are non-conventional designs, and would most likely fail in
the market since customers react negatively to non-conventional designs (Ref. 22).
Figure 5.3.2 shows three
configurations the author has
deemed as suitable choices.
Configurations 10 and 11 have a
conventional wing, fuselage, and
engine attachment. Configuration 10 has a T-tail, while Configuration 12 has a cruciform tail. These were deemed
suitable because they are market-proven and achieve desired handling qualities. Configuration 11 has a conventional
fuselage and a T-tail, but uses a forward swept wing and was deemed suitable because desired handling qualities can
be achieved. It also is less prone to tip stall at low speeds, and provides excellent ramp appeal.
5.3.2.4 Configuration Selection
While the author has deemed all three designs in Figure 5.3.2 to be suitable, the author does not have enough
time to perform an in depth analysis of each configuration. Configuration 10 is market-proven, has relatively low
manufacturing costs, and provides excellent ramp appeal. Therefore, the author has selected to use Configuration 10.
5.4 Configuration Summary and Recommendation
5.4.1 Configuration Summary
The author summarizes that:
 The aircraft will have a low cantilever wing,
with aft sweep and winglets.
 Two turbofan engines will be mounted rear
of the aft pressure bulkhead on the fuselage.
 A T-tail will be used.
 A conventional fuselage will be used.
 Conventional retractable landing gear be
used.
5.4.2 Configuration Recommendations
This author recommends that:
 A full in-depth analysis of each suitable configuration be done to select the most appropriate design
configuration.
Figure 5.3.3: Three Most Suitable Configurations

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6 Layout of the Cockpit and Fuselage
The purpose of this chapter is to show the layout and design of the M-Jet Stratosphere’s cockpit and fuselage.
All design procedures come from Chapter 4 of Ref. 19 with supplemental information from Chapter 2 of Ref. 26.
6.1 Layout Design of the Cockpit
The cockpit was designed to seat a 95% male as pilot in command (PIC) and as copilot. The M-Jet Stratosphere
will obtain single pilot certification; therefore, the traditional copilot seat will be used for a passenger. Pilot weight is
defined as 200 lbs by the RFP (Ref. 1), and 95% stature is defined as 73.54 in tall by the U.S. Army Anthropometry
survey (ANSUR) (Ref. 27). Figures 6.1.1, 6.1.2, 6.1.3 show section cuts of the cockpit with dimensions in inches.
Each view shows the maximum and minimum view lines from the PIC’s left eye. Each angle adheres to the standards
set forth in Figure 2.18 of Ref. 26, except maximum azimuth toward the port side, which is designed to 115°. The
required maximum port azimuth is 135° (Fig. 2.18, Ref. 26), therefore the author recommends synthetic vision be
used to compensate the last 20°. Figure 6.1.4 shows the Visibility pattern for the M-Jet Stratosphere, along with the
ideal visibility pattern. Figures 6.1.5 and shows isometric views of the cockpit.
Figure 6.1.1: Cockpit Side View (Scale 1:30) Figure 6.1.2: Cockpit Top View (Scale 1:30)
Figure 6.1.3: Cockpit Front View (Scale 1:30) Figure 6.1.4: PIC Visibility Chart (Ref.

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6.2 Layout of the Fuselage
Layout design of the fuselage followed procedures from Chapter 4 of Ref. 26. The fuselage was designed to
meet the specifications of the RFP (Ref. 1). The two largest design drivers were the eight passenger, and 60 ft3
baggage
space requirements. Although empty space in the fuselage was minimized; eight passengers can inhabit the fuselage,
with one in the copilot seat, and seven in the main cabin. The passengers shown consist of 50%, 75%, and 90% stature
males and females (Ref. 27). The cabin also features an externally serviceable lavatory. The total baggage capacity
is 61 ft3
, with 6.2 ft3
in each galley cabinet, 15 ft3
in the lavatory, and 33.6 ft3
in the rear baggage compartment. The
structural depth of the fuselage is 1.5 inches. Figure 6.2.1 shows a side view with key dimensions, also shown in Table
6.2.1. Figures 6.2.2, 6.2.3, and 6.2.4 show exterior views with dimensions, and Figures 6.2.5, 6.2.6, 6.2.7 show section
views of the interior. Figures 6.2.8 and 6.2.9 show isometric views. All FS, WL, and BL dimensions are in inches.
Table 6.2.1: Fuselage Dimensions
df (in) 62
lf (in) 525
lfc (in) 200
θfc (°) 12
Figure 6.2.1: Fuselage Dimension (Scale 1:100)
Figure 6.2.2: Fuselage Side View (Scale 1:100)
Figure 6.2.4: Fuselage Front
View (Scale 1:30)Figure 6.2.3: Fuselage Top View (Scale 1:30)
Figure 6.1.5: Cockpit Isometric Views (No Scale)

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Galley Lavatory Rear Baggage Compartment
6.3 Cockpit and Fuselage Summary and Recommendations
6.3.1 Cockpit and Fuselage Summary
This author summarizes that:
 df = 62”
 lf = 525”
 lfc = 200”
 θfc = 12°
 Total Baggage Volume = 61 ft3
 Structural Depth = 1.5”
 Cockpit modeling is simplified for this report
 1.5 zone club seating in cabin
 One jump-seat for passenger
 One passenger in copilot seat, 95% male
 One pilot, 95% male
 Externally serviceable lavatory
6.3.2 Cockpit and Fuselage Recommendations
This author recommends that:
 Seats be modeled with additional detail to take advantage of full cabin width.
50% Male
75% Male
90% Male50% Female
75% Female
90% Female95% Male
Figure 6.2.5: Cabin Side View, with Section Labels (Scale 1:80)
Figure 6.2.6: Cabin Top View, with Passenger Labels (Scale 1:80)
Figure 6.2.8: Cabin Cross Section (Scale 1:30) Figure 6.2.7: Fuselage Isometric View (No Scale)

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7 Layout Design of the Propulsion Installation
The purpose of this chapter to is show the selected propulsion unit and how it will be installed on the M-Jet
Stratosphere. Procedures for selection of the propulsion unit and layout of the propulsion installation come from
Chapter 5 of Ref. 19
7.1 Selection and Layout of the Propulsion Installation
The two most common propulsion types for business jets are turbojets and turbofans. Since the RFP is for a
light business jet, only these two propulsion types were considered. The mission specification requires aggressive
range requirements; therefore, a turbofan was selected as the propulsion type for the M-Jet Stratosphere. Figure 7.1.1
has the design region shown by a red circle, and confirms the turbofan selection.
To follow the light
business jet market, and to
meet FAR Part 25
certification, the author chose
to use two engines. From
Chapter 4, the required thrust
was found to be 5421 lbs
which leads to a minimum
thrust of each engine to 2711
lbf. The author has chosen to
use two Williams
International FJ44-3 turbofan
engines, because they meet the thrust requirements and perform well at altitude (Ref. 22). The FJ44-3 has a length of
48 in, diameter of 23 in, and is rated for a 3000 lb thrust class (Ref. 28). The engine location was selected to be fuselage
mounted, rear of the aft pressure bulkhead to protect against a possible rotor non-containment event and to keep with
industry standards. The engine installations are compatible with all requirements of Step 5.11, p. 134 of Ref. 19.
Figures 7.1.2, 7.1.3, and 7.1.4 show views of the engines with FS, WL, and BL dimensions, all in inches. These views
show a simplified engine, with hard points shown in red dots. Figures 7.1.5 and 7.1.6 show isometric views of the
engine.
Figure 7.1.1: Mach vs. Altitude Chart for Various Engine Types (Fig. 5.1, p.
124, Ref. 19)

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7.2 Propulsion Summary and Recommendations
7.2.1 Propulsion Summary
The author summarizes that:
 Two Williams International FJ44-3 turbofans be used.
 The engines be mounted on the fuselage, rear of the aft pressure bulkhead.
7.2.2 Propulsion Recommendations
This author recommends that:
 The engine pylon attachment to the fuselage be designed in more detail to uphold structural loads.
Figure 7.1.2: Engine Front View (Scale 1:10) Figure 7.1.3: Engine Top
View (Scale 1:20)
Figure 7.1.4: Engine Side View (Scale 1:16)
Figure 7.1.5: Engine Isometric View
(No Scale)

28. Aerospace Engineering Department 28
8 Class I Layout Design of the Wing
The purpose of this chapter is to determine layout design of the M-Jet Stratosphere’s wing. Procedures for Class
I Wing Design are from Chapter 6 of Ref. 19.
8.1 Wing Design Layout
The M-Jet Stratosphere will use a cantilever wing because a strut or braced wing is extremely impractical for
a high-speed aircraft like the Stratosphere. The wing/fuselage arrangement will be a low wing, to take advantage of
the relatively easy manufacturing practices and allow for a simpler fuselage and wing design. This will also allow the
landing gear weight to be minimized. Since this aircraft requires a HSC of Mach 0.85, a super critical airfoil will be
used to decrease wave drag at transonic speeds. To determine the quarter-chord sweep angle, Λc/4, CLcruise was
calculated from Eq. 6.1 of Ref. 19 and was found to be 0.4; the hand calculation can be seen here. Various parameters
from Chapters 3 and 4 were used for this calculation, and can be seen in Table 8.1.1. Since a supercritical airfoil will
be used, Mcr can be decreased by 0.05 for use in Figure 6.1b from Ref. 19. To increase fuel volume, a thickness-to-
chord ratio (t/c) of 12% has been selected. Using Mcr of 0.75, CLcruise of 0.4, and t/c of 12%, the wing sweep was found
to be 27 degrees using Figure 6.1b of Ref. 19. To meet the thickness-to-chord ratio, and the super critical airfoil
requirement, the author has selected to use a NASA SC(2)-0712 airfoil, which is shown in Figure 8.1.1. This is a
supercritical airfoil, with a max t/c of 12%.
Table 8.1.1: Key Aircraft Parameters
To select a taper ratio (λw), dihedral angle (Γw), incidence angle (iw), and washout out angle (εw), Table 6.5 of
Ref. 19 was used. These values were selected based off historical trends that have proven successful in the market.
The author selected a taper ratio of 0.35, and a dihedral, incidence, and washout angle of 0°. The incidence angle may
be changed after a stability and control report to allow the jet to cruise with a zero angle of attack. The root chord was
found to be 714 ft using Eq. 2.8 from Ref. 30, the tip chord was found to be 2.5 ft using the taper ratio, and the
wingspan, b, was found to be 42.4 ft using Eq. 2.7 from Ref. 30. Hand calculations for this can be seen here.
The total fuel weight for a LRC mission was found to be 4065 lbs in Chapter 3. This equates to a required
volume of 77.3 ft3
, and hand calculations can be seen here. The Stratosphere’s wing will hold fuel between the main
forward and rear spars, as well as in the leading edge and aft of the rear spar where there are no control surfaces or
Takeoff Weight (lbs) 13900
Fuel Weight (lbs) 4065
LRC Mach Number (~) 0.8
Dynamic Pressure, LRC (psf) 138.5
Wing Area, S (ft2
) 204.4
Aspect Ratio, AR (~) 8.8
Figure 8.1.1: NASA SC(2)-0712 Airfoil Profile (Ref. 29)

29. Aerospace Engineering Department 29
high lift devices. The leading edge will be armored to protect against a bird strike rupturing the fuel tank. It will be
electrically heated to allow maximum space for fuel. Total fuel volume of the wing was found using two methods.
The first using the space finder function in NX, the second by multiplying the average of the front and rear face area
by the length of the tank. The first method yielded a volume of 75.6 ft3
, and the second yielded a fuel volume of 84.2
ft3
. Hand calculations of the second
method and can be seen here. Since
both of these methods are
approximations, and are well within
10% of the required volume, the
author has determined there is
sufficient fuel volume. Additional
fuel volume can be created by storing
fuel in the wing-fuselage strake
fairing. Figure 8.1.2 shows half the
span of the wing with the fuel tank
exposed, as well as showing the forward and rear spar lines.
Figures 8.1.3, 8.1.4, and 8.1.5 show views of the Stratosphere’s wing with FS, BL, and WL dimensions, all in
inches. Figure 8.1.6 shows an isometric view of the wing and an isometric view of the wing installed on the fuselage.
Figure 8.1.2: Half Span with Exposed Fuel Tank and Spar
Lines (Scale 1:40)
Figure 8.1.3: Wing Top View (Scale 1:50)

30. Aerospace Engineering Department 30
8.2 Wing Design Summary and Recommendations
8.2.1 Wing Design Summary
This author summarizes that:
 The wing is a low,
cantilever wing.
 The NASA SC(2)-0712
airfoil be used
 S = 204.4 ft2
 AR = 8.8
 b = 42.4 ft
 Λc/4 = 27°
 t/c = 12%
 λw = 0.35
 Γw = 0°
 iw = 0°
 εw = 0°
 Cr = 7.14 ft
 Ct = 2.50 ft
 Fuel Volume Required
= 77.3 ft3
 Actual Fuel Volume =
75.6 ft3
(Method 1) or
84.2 ft3
(Method 2)
8.2.2 Wing Design Recommendations
This author recommends that:
 The wing incidence angle be changed to allow a zero angle of attack in cruise conditions.
 The leading edge be armored to protect fuel from possible bird strikes.
 Additional fuel be stashed in the wing-fuselage strake fairing.
Figure 8.1.5: Wing Side View (Scale 1:20)
Figure 8.1.4: Wing Isometric Views (No Scale)

31. Aerospace Engineering Department 31
9 Class I Design of High Lift Devices
The purpose of this chapter is to layout the design and size of the M-Jet Stratosphere’s high lift devices. Methods
for Class I High Lift Devices Design follow Chapter 7 of Ref. 19 and p. 168-180 of Ref. 31.
9.1 Design of High Lift Devices
Chapter 4 of this report selected CLmax(need) values for cruise (clean), takeoff,
and landing based off procedures from Ref. 15, and can be seen in Table 9.1.1. To
determine how much ∆CLmax the flap needs to create, the CLmax that the wing already
creates will be found subtracted from the values in Table 9.1.1 (p. 167, Ref. 31).
Methods from p. 168-172 of Ref. 31 were used in conjunction with Figure
7.1 of Ref. 19 to determine the CLmax that the wing already creates. CLmax(have) values
for each condition were found, and are shown in Table 9.1.1. Hand calculations
showing how these values were found can be seen here.
The ∆CLmax for each condition was found using Eq. 7.6, 7.7 from Ref. 19 and Eq. 7.6-
from Ref. 31. Hand
calculations for this can be seen here, and values are shown in Table 9.1.1. While CLmax for cruise is small, it is
negligible because Figure 7.1 from Ref. 19 shows no supercritical airfoil data, so four and five digit airfoil curves
were used to be conservative. Clmax values are very similar to the maximum given by Ref. 29, even though Ref. 29
shows them at a Reynold’s number of 1E+06 and this data is for a Reynold’s number 8.6E+06. Clmax increases with
increased Reynold’s number, as shown in Ref. 29,
and therefore, this airfoil will generate sufficient lift
in cruise without flaps. This also means that the high
lift devices are sized conservatively and will generate
more lift than expected in real flight conditions.
The author has selected fully aft translating Fowler flaps to generate ∆Cl(need) for the airfoil. A isometric view
the Stratosphere’s of Fowler flaps is shown in Figure 9.1.1. ∆Cl(need) was calculated using Eq. 7.11 and Figure 7.4 from
Ref. 19. Hand calculations for this can be seen here, and these values are shown in Table 9.1.4. Based on current
business jet designs, the author has selected flaps that span from 13% to 65% of the half span. Then, Eq. 7.14 and 7.17
along with Figure 7.8 from Ref. 19 were used to determine required flap chord and deflection, and hand calculations
can be seen here. To produce the required ΔCl, the author has decided to droop the Stratosphere’s ailerons to also act
Figure 9.1.1: Fully Aft Translating Fowler Flap (No Scale)
Table 9.1.1: Various Lift
Coefficients
CLmax(need) (~) 1.4
CLmaxTO(need) (~) 2
CLmaxL(need) (~) 2.8
CLmax(have) (~) 1.38
CLmaxTO(have) (~) 1.36
CLmaxL(have) (~) 1.36
ΔCLmax (~) 0.02
ΔCLmaxTO (~) 0.67
ΔCLmaxL (~) 1.51
ΔCl(need)Clean (~) 0.026
ΔCl(need)TO (~) 1.041
ΔCl(need)L (~) 2.339

32. Aerospace Engineering Department 32
as flaps during takeoff and landing. Based on current business jet designs, the author has selected ailerons to span
from 70% to 99% of the half span. Table 9.1.5 and 9.1.6 show the results of high lift device sizing that are not already
displayed in previous tables. Figure 9.1.2 shows a top view of the Stratosphere’s wing, with high lift device FS and
BL dimensions in inches. The spreadsheet used for these calculations can be seen here.
9.2 High Lift Devices Summary and Recommendations
9.2.1 High Lift Devices Summary
This author summarizes that:
 Fully aft translating Fowler flaps be used in conjunction with drooped ailerons, with cf/c=0.25
 Flap deflection for takeoff is 20º, and flap deflection for landing is 45º
 Flaps span from 13% to 65%, and drooped ailerons span from 70%-99% of the half span
9.2.2 High Lift Devices Recommendations
This author recommends that:
 Accurate data for the NASA SC(2)-0712 be created for high Reynold’s number flap size can be reduced
 A more detailed CAD model of the flaps be created
Table 9.1.2: High Lift Device Sizing Results
Rnr (TO and Landing) (~) 8.39E+06
Rnt (TO and Landing) (~) 2.94E+06
Clmax(root) (TO and Landing) (~) 1.75
Clmax(tip) (TO and Landing) (~) 1.6
CLmax,unswept (TO and Landing) (~) 1.6
kλ (~) 0.96
λ (~) 0.35
CLmax,swept (TO and Landing) (~) 1.43
ΔClmax (TO) (~) 1.02
ΔClmax (Landing) (~) 2.29
KΛ(~) 0.86
Swf/S (~) 0.77
ηi flap (~) 0.13
ηo flap (~) 0.65
Table 9.1.3: High Lift Device Sizing Results
ηi drooped aileron (~) 0.70
ηo drooped airleron (~) 0.99
KFowler (~) 0.98
cf/c (~) 0.25
Clαf (1/rad) 7.85
Clα (1/rad) 6.28
δf takeoff (deg) 20
αδf takeoff 0.48
ΔCl,actual takeoff (~) 1.132
δf landing (deg) 45
αδf landing (rad) 0.38
ΔCl,actual landing (~) 2.344
Figure 9.1.2: Wing Top View with High Lift Device Dimensions (Scale 1:100)

33. Aerospace Engineering Department 33
10 Class I Design of Empennage
The purpose of this chapter is to outline the design of the M-Jet Stratosphere’s empennage. Design procedures
follow Chapter 8 from Ref. 19 with supplemental information from p. 8-24 from Ref. 32.
10.1 Empennage Design Procedures
The Stratosphere will utilize a T-tail design, as it will allow the vertical tail to be shorter and will keep the
horizontal tail out of the jet blast, as well as reducing downwash effects. In addition, this T-tail design follows business
jet industry standards. Both the horizontal and vertical tail use a NACA 0012 symmetric airfoil. To size the tail, Table
8.5a and 8.5b from Ref. 19 were used to select a horizontal and vertical tail volume coefficient, V̅ h and V̅ v, respectively.
These tail volume coefficients
were based off of Cessna Citation
tail volume coefficients, which are
comparable business jets. Then,
equation 8.3 and 8.4 from Ref. 19
were used to find empennage
areas. For both the horizontal and
vertical tail, historical inference
was used to select root and tip
chords, vertical tail sweep angle,
and rudder/elevator chord percent.
Then span was found using Eq. 2.8
from Ref. 30. The horizontal tail
sweep angle was selected to be
higher than the wing sweep angle so that the tail will stall after the wing. The incidence, dihedral and downwash angles
were selected to be 0° for both the horizontal and vertical tail. Incidence angle of the horizontal may change after a
stability and control analysis. Table 10.1.1 shows salient characteristics of the empennage. Hand calculations for class
I empennage design can be seen here, and the spreadsheet used for calculations can be seen here. Figures 10.1.1
through 10.1.7 show different views of the empennage.
Figure 10.1.3: Horizontal Tail Front View (Scale 1:25)
Table 10.1.1: Empennage Salient Characteristics
V̅ (~) Span (ft) Cr (ft) Ct (ft) λ (~) Λc/4 (°)
Horizontal Tail 0.80 10 4 2 0.50 31
Vertical Tail 0.07 6 6 4 0.67 49
Figure 10.1.2: Horizontal Tail Top View (Scale 1:25)
Figure 10.1.1: Horizontal Tail Side View (Scale 1:20)

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10.2 Empennage Design Conclusion and Recommendations
10.2.1 Empennage Design Conclusions
This author concludes that:
 A T-tail configuration be used
 V̅ h = 0.80, V̅ v = 0.07
 bh = 10 ft, bv = 6 ft
 Cr,h = 4 ft, Ct,h = 2 ft
 Cr,v = 6 ft, Ct,v = 4 ft
 Λc/4,h = 31°, Λc/4,v = 49°
10.2.2 Empennage Design Recommendations
This author recommends that:
 The rudder and elevator chord be determined from stability and control analysis
 More detailed sizing analysis be performed
Figure 10.1.6: Vertical
Tail Front View
Figure 10.1.5: Vertical Tail Side View (Scale 1:25)
Figure 10.1.4: Vertical Tail Top View (Scale 1:20)
Figure 10.1.7: Empennage Isometric View (No Scale)

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11 Class I Design of the Landing Gear
The purpose of this chapter is to describe the design of the M-Jet Stratosphere’s landing gear. Design procedures
follow Chapter 9 from Ref. 19 with supplemental information from p. 26-43 from Ref. 32.
11.1 Landing Gear Design Procedure
The Stratosphere will use retractable landing gear to reduce drag in flight. The landing gear will be in a
conventional tricycle configuration because that is the industry standard. To select the initial location of the landing
gear, a preliminary CG was determined and can be seen here. The preliminary CG yielded a landing gear location that
was used in a class I weight and balance analysis. After the weight and balance analysis was completed (see Chapter
12 for complete analysis) the final landing gear location was found using the new CG information. The landing gear
was placed to follow requirements for longitudinal and lateral tip-over as well as ground clearance criteria, as laid out
in Chapter 8 of Ref. 19. The static load for each strut was found using Eq. 9.1 and 9.2 from Ref. 19, then their ratio to
WTO was found. The number of wheels was selected based off of Table 9.1 of Ref. 19. Table 11.1.1 shows salient
characteristics of the landing gear. Hand calculations for landing gear sizing can be seen here, and the spreadsheet can
be seen here.
The nose gear is attached to
the forward pressure bulkhead,
and retracts forward into the nose.
The main gear are located under
the wing, and retract forward. The
the wheel rotates 90 degrees as it
folds into the wing.
Figures 11.1.1 through
11.1.6 show various
views of the landing gear.
Figure 11.1.1 shows
Table 11.1.1: Landing Gear Salient Characteristics
lm
(ft)
ln
(ft)
Pm
(lbf)
Pn
(lbf)
Pm/WTO
(~)
Pn/WTO
(~)
MG
Diameter
(in)
MG
Width
(in)
MG
Pressure
(psi)
NG
Diameter
(in)
NG
Width
(in)
NG
Pressure
(psi)
1.32 15.1 6391 1119 0.92 0.08 22 6 95 18 5.7 120
Figure 11.1.1: Landing Gear Front View (Scale 1:100)
Figure 11.1.2: Landing Gear Side View (Scale 1:100)

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adherence to lateral ground clearance requirements. Figure 11.1.2 shows adherence to the 15° rotation angle, 15°
longitudinal tip-over angle, and 15° flow separation angle. Figure 11.1.4 shows adherence to the lateral tip-over
requirement.
To fit the landing gear inside the wing, fuel volume was sacrificed. The original fuel volume before the landing
gear was 75.6 ft3
using NX’s volume function. To regain lost fuel volume, the author chose to create nose and
empennage fuel tanks. The nose tank is in front of the forward pressure bulkhead above the nose gear storage. The
empennage fuel tank is aft of the empennage baggage compartment, through the centerline of the tail cone. The nose
fuel tank holds 8.4 ft3
of fuel and the empennage tank holds 6.6 ft3
. After creating a landing gear compartment in the
wing, there is 62.4 ft3
left in the wing fuel tank. This creates a total fuel volume of 77.4 ft3
, which meets the
requirement. Figure11.1.7 shows these fuel tanks.
Figure 11.1.3: Landing Gear Top View (Scale 1:200)
Figure 11.1.4: Landing Gear Isometric View (No Scale)
Figure 11.1.6: Nose Gear Retracted (No Scale)
Figure 11.1.5: Main Gear Retracted (No Scale)

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11.2 Landing Gear Conclusions and Recommendations
11.2.1 Landing Gear Conclusions
The author concludes that:
 The landing gear be retractable and in a tricycle configuration
 The landing gear meets lateral and longitudinal tip-over requirements and rotation requirements
11.2.2 Landing Gear Recommendations
The author recommends that:
 The landing gear be CAD in further detail
Figure 11.1.7: Nose and Empennage Fuel Tanks (No Scale)