Propeller of Aircraft.

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2. Cessna 425 Aircraft
Program: BS-AMT Semester: 8th
Presented To: Dr. Saqib Hameed Course: Propeller
Presented By: Omer Ishfaq Reg No: 70074041

3. Discussion Points
 Introduction
 Specifications Cessna 425 Corsair
 Construction
 Aerodynamics of Propeller
 Working Principle
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4. Introduction
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The Cessna 425, known as the Corsair and later
as the Conquest I, is an eight-seat American
pressurized turboprop twin-engine light aircraft.
The 425 was introduced as a competitor to
the Beechcraft King Air.

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6. Specifications Cessna 425 Corsair
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General characteristics
 Crew: two pilots
 Capacity: four–six passengers
 Length: 35 ft 10+1⁄4 in (10.93 m)
 Wingspan: 44 ft 1+1⁄2 in (13.45 m)
 Height: 12 ft 7+1⁄4 in (3.84 m)
 Wing area: 224.98 sq. ft (20.901 m2)
 Airfoil: NACA 23018-63 (mod) at root, NACA 23009-63 at tip
 Empty weight: 4,915 lb (2,229 kg)
 Max takeoff weight: 8,200 lb (3,719 kg)
 Fuel capacity: 366 US gal (305 imp gal; 1,390 L) usable capacity
 Powerplant: 2 × Pratt & Whitney Canada PT6A-112 turboprops, 450 shp (340 kW) each
 Propellers: 3-bladed Hartzell 9910438-1 or McCauley 9910535-1 constant-speed propellers

7. Conti..
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Performance
 Maximum speed: 264 kn (304 mph, 489 km/h) at 17,700 ft (5,400 m)
 Cruise speed: 210 kn (240 mph, 390 km/h) at 30,000 ft (9,100 m), econ cruise
 Stall speed: 79 kn (91 mph, 146 km/h) (CAS),flaps and undercarriage down, engines idling
 Range: 1,646 nmi (1,894 mi, 3,048 km) at 30,000 ft (9,100 m), econ cruise, 45 min reserves
 Service ceiling: 34,700 ft (10,600 m)
 Rate of climb: 2,027 ft/min (10.30 m/s)
 Takeoff run to 50 ft (15m): 2,431 ft (741 m)
 Landing run from 50 ft (15 m): 2,145 ft (654 m)

8. Construction
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The Hartzell ASC-II consists of a unique
monocoque structure of advanced composite
materials. The structure consists of carbon fiber
laminates integrated into a co-molded stainless
steel shank. The outboard half of the leading
edge is protected with a co-molded electroformed
nickel erosion shield.

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11. Aerodynamics of Propeller
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Aerodynamically, thrust is the result of the propeller shape
and the AOA of the blade. Thrust can be considered also in
terms of the mass of air handled by the propeller. In these terms,
thrust equals mass of air handled multiplied by slipstream
velocity minus velocity of the aircraft.

12. Working Principle
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The propeller has a natural tendency to slow down
as the aircraft climbs and to speed up as the aircraft
dives because the load on the engine varies. To
provide an efficient propeller, the speed is kept as
constant as possible. By using propeller governors
to increase or decrease propeller pitch, the engine
speed is held constant. When the airplane goes into
a climb, the blade angle of the propeller decreases
just enough to prevent the engine speed from
decreasing. The engine can maintain its power
output if the throttle setting is not changed. When
the airplane goes into a dive, the blade angle
increases sufficiently to prevent overspeeding and,
with the same throttle setting, the power output
remains unchanged.

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