In: Mechanical Engineering
(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.
(1) True: A shockwave is a thin region of highly viscous flow, and flow through the shock is adiabatic but nonisentropic.
(2) True: The specific heat ratio of air for hypersonic flow is constant. However its not equal to value as in normal condition. It should be decreased to close to 1.
(3) False: Normal shocks are substantially perpendicular to the flow and oblique shocks are inclined at any angle.
(4) False: NACA 2412 has maximum camber of 2% at 40% chord whereas NACA 0015 has maximum camber of 0% at 0% chord.
(5) True: Critical mach number is the is the lowest mach number at which the aircraft reaches the speed of sound.