Objective • This project validated and analyse NACA0012 airfoil. We are using ANSYS Fluent. • Calculate drag and lift coefficient at the airfoil Airfoil file copy and save as .txt #Group #Point #X #Y #Z 1 1 1 0 0 1 2 0.998459 0.000224 0 1 3 0.993844 0.000891 0 1 4 0.986185 0.00199 0 1 5 0.975528 0.003501 0 1 6 0.96194 0.005399 0 1 7 0.945503 0.007651 0 1 8 0.92632 0.010221 0 1 9 0.904508 0.013071 0 1 10 0.880203 0.016158 0 1 11 0.853553 0.019438 0 1 12 0.824724 0.022869 0 1 13 0.793893 0.026405 0 1 14 0.761249 0.03 0 1 15 0.726995 0.03361 0 1 16 0.691342 0.037188 0 1 17 0.654508 0.040686 0 1 18 0.616723 0.044055 0 1 19 0.578217 0.047242 0 1 20 0.53923 0.050196 0 1 21 0.5 0.052862 0 1 22 0.46077 0.055184 0 1 23 0.421783 0.057108 0 1 24 0.383277 0.058582 0 1 25 0.345492 0.059557 0 1 26 0.308658 0.059988 0 1 27 0.273005 0.059841 0 1 28 0.238751 0.059088 0 1 29 0.206107 0.057712 0 1 30 0.175276 0.055708 0 1 31 0.146447 0.053083 0 1 32 0.119797 0.049854 0 1 33 0.095492 0.046049 0 1 34 0.07368 0.041705 0 1 35 0.054497 0.036867 0 1 36 0.03806 0.03158 0 1 37 0.024472 0.025893 0 1 38 0.013815 0.019854 0 1 39 0.006156 0.013503 0 1 40 0.001541 0.006877 0 1 41 0 0 0 1 42 0.001541 -0.006877 0 1 43 0.006156 -0.013503 0 1 44 0.013815 -0.019854 0 1 45 0.024472 -0.025893 0 1 46 0.03806 -0.03158 0 1 47 0.054497 -0.036867 0 1 48 0.07368 -0.041705 0 1 49 0.095492 -0.046049 0 1 50 0.119797 -0.049854 0 1 51 0.146447 -0.053083 0 1 52 0.175276 -0.055708 0 1 53 0.206107 -0.057712 0 1 54 0.238751 -0.059088 0 1 55 0.273005 -0.059841 0 1 56 0.308658 -0.059988 0 1 57 0.345492 -0.059557 0 1 58 0.383277 -0.058582 0 1 59 0.421783 -0.057108 0 1 60 0.46077 -0.055184 0 1 61 0.5 -0.052862 0 1 62 0.53923 -0.050196 0 1 63 0.578217 -0.047242 0 1 64 0.616723 -0.044055 0 1 65 0.654508 -0.040686 0 1 66 0.691342 -0.037188 0 1 67 0.726995 -0.03361 0 1 68 0.761249 -0.03 0 1 69 0.793893 -0.026405 0 1 70 0.824724 -0.022869 0 1 71 0.853553 -0.019438 0 1 72 0.880203 -0.016158 0 1 73 0.904508 -0.013071 0 1 74 0.92632 -0.010221 0 1 75 0.945503 -0.007651 0 1 76 0.96194 -0.005399 0 1 77 0.975528 -0.003501 0 1 78 0.986185 -0.00199 0 1 79 0.993844 -0.000891 0 1 80 0.998459 -0.000224 0 1 0

1. www.engineeringwithsandeep.com| Student Assignment
Assignment No. 9
Airfoil Analysis(NACA 0012 )
05.05.2021
Shivam Choubey
Student No: CFDB30321004

2. www.engineeringwithsandeep.com| Student Assignment
Objective
• This project validated and analyse NACA0012 airfoil. We are
using ANSYS Fluent.
• Calculate drag and life cofficent at airfoil.

3. www.engineeringwithsandeep.com| Student Assignment
Problem Statement
Inlet
outlet
Airfoil
R15 m
30 m
1m
The fundamental problem we are attempting to solve is the modelling of a 2D airfoil cross
section. Given the below figure, We can determine the lift and drag acting on the airfoil.
For our airfoil, we are working in the turbulent regime, with Re = 6*10^6. Our speed is M=0.15,
which converts to about 51 m/s. This region is essentially incompressible.

4. www.engineeringwithsandeep.com| Student Assignment
CFD Setting
Mesh Quality
Max skewness 0.78211
Max Aspect ratio 787.91
Mesh staatistics
No of nodes 24967

5. www.engineeringwithsandeep.com| Student Assignment
CFD Setting
• Consider Pressure Based, Steady Flow and Planar
Simulation(Mech Number is almost 0.1)
• Consider SST k-w turbulence model
• Working fluid is air (viscosity 1.76E-5) and denstiy
(1.12).
• Velocity of inlet air is 43 m/s.
• Angle of attach is 10 degree(angle b/w air and cord length).

6. www.engineeringwithsandeep.com| Student Assignment
Results
Cd = 0.08633 Cl =0.50279
AOA 10 degree
Velocity 43 m/s
Drag Cofficent
Lift cofficent
Velocity
Pressure

7. www.engineeringwithsandeep.com| Student Assignment
Cd = 0.2519 Cl =0.65779
AOA 20 degree
Velocity 43 m/s
Drag Cofficent
Lift cofficent
Velocity
Pressure

8. www.engineeringwithsandeep.com| Student Assignment
Conclusion
• Our model was validated for lift and drag. It shows very close
agreement to the NASA Langley Center’s data(Error 5 %),
which includes wind tunnel and software testing.
• We have successfully modeled an airfoil’s lift in ANSYS Fluent
to a very high degree of accuracy.
• However, our drag and lift results had some disagreements
with the NASA results. Although we maintained the same
overall shape.
• When AOA is increasing Cd and Cl also increases.

9. www.engineeringwithsandeep.com| Student Assignment
References
• 2DN00: 2D NACA 0012 Airfoil Validation Case.”
https://turbmodels.larc.nasa.gov/naca0012_val.html
• , NASA Langley Turbulence Modeling Resource, 2015.