Flow over Naca 0017 airfoil section
Flow over NACA 0017 Airfoil
Flow parameters
Flow is transient in nature.
Inlet velocity of flow is 500 m/s.
Case 1
Angle of attack – 0
Flow inlet velocity – 500 m/s
Case 2
Angle of attack – 2
Flow inlet velocity – 500 m/s
Case 3
Angle of attack – 4
Flow inlet velocity – 500 m/s
Case 4
Angle of attack – 6
Flow inlet velocity – 500 m/s
Case 5
Angle of attack – 8
Flow inlet velocity – 500 m/s
Case 6
Angle of attack – 10
Flow inlet velocity – 500 m/s
Comparision of lift and drag forces.
|
Angle of attack |
0 |
2 |
4 |
6 |
8 |
10 |
|
Lift (N) |
Max – 0.162 Min – (-0.224) |
Max –15.087 Min – 14.598 |
Max – 17.873 Min -17.527 |
Max – 26.171 Min – 25.773 |
Max –35.439 Min -35.192 |
Max –43.966 Min -43.786 |
|
Drag (N) |
Max –24.224 Min -24.012 |
Max –24.772 Min – 24.530 |
Max –15.727 Min – 15.614 |
Max – 17.245 Min – 17.079 |
Max –18.800 Min -18.673 |
Max –21.315 Min -21.205 |
As shown in the table above - the values shown are the minimum and maximum values for the lift and drag forces that are created for different angle of attack ( on a naca 0017 airfoil)
If we see the table starting from the angle of attack of zero (0) , it clearly shows that - as the AOA ( angle of attack ) increases Lift force increases and the drag force decreases.
i.e, Lift has maximum value for angle of attak of 10 degrees and minimum at 0 degrees.
similarly drag has maximum value for AOA of 0 degrees and has minimum value for AOA of 4 degrees.