- #1
v_arsha
- 7
- 0
Hello,
I did a wind tunnel test with a NACA 0012 airfoil. And my results showed that the highest lift-to-drag ratio occurred at an angle of 12degrees where as my maximum lift is at 15degrees. I even read somewhere that these values do differ but there was no such explanation as in why is that so..
Can someone please help me out..
Thanks
I did a wind tunnel test with a NACA 0012 airfoil. And my results showed that the highest lift-to-drag ratio occurred at an angle of 12degrees where as my maximum lift is at 15degrees. I even read somewhere that these values do differ but there was no such explanation as in why is that so..
Can someone please help me out..
Thanks