At (alpha=0^{circ}), the minimum pressure coefficient for an NACA 0009 airfoil in low-speed flow is -0.25 .
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At \(\alpha=0^{\circ}\), the minimum pressure coefficient for an NACA 0009 airfoil in low-speed flow is -0.25 . Calculate the critical Mach number for this airfoil using
a. The Prandtl-Glauert rule
b. The (more accurate) Karman-Tsien rule
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