Consider a thin airfoil at a freestream Mach number of 0.2. The suction peak is -0.25. Compute the critical Mach number
Posted: Tue Apr 26, 2022 4:51 pm
Consider a thin airfoil at a freestream Mach number of 0.2. The
suction peak is -0.25. Compute the critical Mach number for this
airfoil at this angle of attack.
suction peak is -0.25. Compute the critical Mach number for this
airfoil at this angle of attack.