Question: Problem 3. [30 points] Blunt Bodyv Flow The figure below shows the steadv supersonic flow of air with = 1.4 past a symmetrical blunt body.

Problem 3. [30 points] Blunt Bodyv Flow The
Problem 3. [30 points] Blunt Bodyv Flow The figure below shows the steadv supersonic flow of air with = 1.4 past a symmetrical blunt body. The free stream conditions are M. = 3, static temperature T.. = 15C and static pressure p__ = 101.3 kPa. The steady supersonic flow produces a curved stationary, symmetrically shaped bow shock wave ahead of and around the body. The shock immediately ahead of the stagnation point O on the body can be assumed to be normal and the overall flow can be assumed inviscid. Immediately behind the shock, near the curved part of the body, the flow becomes subsonic (local Mach number less than one) but then it accelerates around the body until 1t becomes just sonic at the sonic lines, shown as dashed lines, and then supersonic downstream of these lines. (a) Calculate the pressure, temperature and Mach number immediately downstream of the normal part of the shock wave. (b) Calculate the density, temperature and pressure at the stagnation point O on the body. (c) Calculate the temperature, pressure and velocity at point 4 where the sonic line intersects the body. Poo = 1013 kPa . T =159

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