1. The peak suction pressure on an airfoil at 5◦ angle of attack is Cp, min = −1.25 in low-speed flow. Calculate the pressure coefficient at the same point on the airfoil, when the freestream Mach...

1. The peak suction pressure on an airfoil at 5◦ angle of attack is Cp, min = −1.25 in low-speed flow. Calculate the pressure coefficient at the same point on the airfoil, when the freestream Mach number is 0.7 using Prandtl-Glauert compressibility correction.

2. The lift curve slope, cl_α, of an airfoil in incompressible flow is 1.95π rad⁻¹. Calculate the lift curve slope for the same airfoil at Mach 0.75, using Prandtl-Glauert correction.