- #1
Thusithatck
- 13
- 0
I have plotted a lift curve of a NACA 643-418 airfoil section which has a flat region in the lift curve approximately from 11 degrees to 16 degrees. Beyond 16 degrees it completely stalls. Can some explain to me the reason behind this flat region in the lift curve.
The experiment was a force balance method which doesn't record pressure on the airfoil surface. Therefore it is unable to get an idea of this flat region.
I suspect as the flow on the upper surface being completely turbulant from 11 degrees to 16 degrees. Beyond 16 degrees the flow compleyely seperates.
The experiment was a force balance method which doesn't record pressure on the airfoil surface. Therefore it is unable to get an idea of this flat region.
I suspect as the flow on the upper surface being completely turbulant from 11 degrees to 16 degrees. Beyond 16 degrees the flow compleyely seperates.