Quote:
Originally Posted by Piotrsko
The airfoils ZERO LIFT angle can be roughly calculated by an imaginary line from the tail through the high point of the Camber line but the zero lift line is not lowest drag AOA. Any good airfoil ordinate data plot can show the AOA for minimum drag and zero lift.
|
Yes, all the data curves are available -
GOE 222 (MVA H.33) AIRFOIL (goe222-il)