Question

(1) [1 Point] True or False: A shock wave is a thin region of highly viscous flow, and the flow through the shock is adiabatic but nonisentropic.

(2) [1 Point] True or False: For hypersonic flow, the ratio of specific heats for air (??) can be assumed to be constant.

(3) [1 Point] True or False: A normal shock wave is a shock wave that makes an oblique angle with respect to the upstream flow.

(4) [1 Point] True or False: The NACA 2412 airfoil has a maximum camber that is less than a NACA 0015 airfoil.

(5) [1 Point] True or False: The critical Mach number is the free stream Mach number at which supersonic flow will occur at a point on the airfoil.

Answer 1