Consider a thin airfoil at a freestream Mach number of 0.2. The suction peak is -0.25. Compute the critical Mach number

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answerhappygod
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Consider a thin airfoil at a freestream Mach number of 0.2. The suction peak is -0.25. Compute the critical Mach number

Post by answerhappygod »

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.
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