At (alpha=0^{circ}), the minimum pressure coefficient for an NACA 0009 airfoil in low-speed flow is -0.25 .

Question:

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

Fantastic news! We've Found the answer you've been seeking!

Step by Step Answer:

Related Book For  book-img-for-question
Question Posted: