Flow over NACA0017 at different Angle of attack

The NACA four-digit wing sections define the profile by:

First digit describing maximum camber as percentage of the chord. Second digit describing the distance of maximum camber from the airfoil leading edge in tens of percents of the chord. Last two digits describing maximum thickness of the airfoil as percent of the chord.

Co ordinates for NACA 0017 profile were generated to .txt file and loaded in

solidworks software.Simulation was conducted to get drag and lift generated at different Angle of Attacks (AoA).

We concluded that at \" 0 Aoa\" drag and lift were min and as AoA increased upto

AoA=10 drag and lift increased.

Angle of Attacks

@10 degree

@AoA 8

@AoA 6

@AoA 6

@AoA 2

@AoA 0