(1) [1 Point] True or False: A shock wave is a thin region ofhighly viscous flow, and the flow through the shock is adiabaticbut nonisentropic.
(2) [1 Point] True or False: For hypersonic flow, the ratio ofspecific heats for air (??) can be assumed to be constant.
(3) [1 Point] True or False: A normal shock wave is a shock wavethat makes an oblique angle with respect to the upstream flow.
(4) [1 Point] True or False: The NACA 2412 airfoil has a maximumcamber that is less than a NACA 0015 airfoil.
(5) [1 Point] True or False: The critical Mach number is thefree stream Mach number at which supersonic flow will occur at apoint on the airfoil.
