Flow over an airfoil
Aim: The Aim of this project is to perform flow simulation over the airfoil for different angles of attack and analyze the results.
Procedure:
- Firstly I started by creating the aerofoil from the aerofoil data. the aerofoil that I have chosen is NACA0017.
- I started flow simulation over the aerofoil with an initial velocity of 700m/s at an Angle of attack of 0 degrees and then I varied the angle of attack from 2,4,6,8,10.
- Analyzed the lift and drag forces for different angles of attacks
Results:
- AOA- 0deg
2. AOA - 2deg
3. AOA -4deg
4. AOA - 6
5. AOA - 8deg
6. AOA - 10deg
Results Discussion
|
AOA |
Drag |
Lift |
|
0 |
0.003 |
1.788*E^-06 |
|
2 |
0.004 |
0.003 |
|
4 |
0.003 |
0.009 |
|
6 |
0.004 |
0.013 |
|
8 |
0.005 |
0.0017 |
|
10 |
0.007 |
0.022 |
As above mentioned the results of lift and drag generated by the airfoil for different angles of attack we can observe that as the angle of attack increases the lift and drag correspondingly increases. our simulation results also follow the same relation which corresponds that the results are Accurate