(1) [1 Point] True or False: A shock wave is a thin region of highly viscous flo
ID: 2086903 • Letter: #
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 (y) can be (3) [1 Point] True or False: A normal shock wave is a shock wave that makes an oblique angle (4) [1 Point] True or False: The NACA 2412 airfoil has a maximum camber that is less than a assumed to be constant. with respect to the upstream flow. NACA 0015 airfoil. 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. (5) [1Explanation / Answer
1. False. A shock wave is a thin region of highly viscous flow and flow through the shock is adiabatic and isentropic.
2.False. For low speeed flows ratio of specific heats are assumed to be constant. But for a hypersonic floe ratio of specific heats are not a constant.
3.False. A normal shock wave is a shock wave that makes right angle with the upstream flow.
4. False. A NACA 2412 has a maximum camber of 2% and NACA 0015 has a maximum camber of 0%
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