Question 4: In the the test section of a supersonic wind tunnel, a 10° half-angle wedge is tested at zero angle of attack. When the tunnel is operating, the wave angle from the wedge leading edge is measured to be 30°. a) What is the exit-to-throat area ratio of the tunnel nozzle? b) What is the drag coefficient for this wedge? Question 5: Consider the isentropic flow through a subsonic diffuser with an exit to entry area raio of 4.0. The Mach number of the free stream flow is 2.0 with total pressure of 1atm and total temperature 300K. There is a standing normal shock before the entry of the diffuser. Calculate the Mach number and temperature at the exit of the diffuser.
Added by Harold F.
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M=2.0, T=300K Show more…
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Supreeta N.
A supersonic wind tunnel is to be operated at $M=2.2$ in the test section. Upstream from the test section, the nozzle throat area is $0.07 \mathrm{m}^{2} .$ Air is supplied at stagnation conditions of $500 \mathrm{K}$ and $1.0 \mathrm{MPa}$ (abs). At one flow condition, while the tunnel is being brought up to speed, a normal shock stands at the nozzle exit plane. The flow is steady. For this starting condition, immediately downstream from the shock find (a) the Mach number, (b) the static pressure, (c) the stagnation pressure, and (d) the minimum area theoretically possible for the second throat downstream from the test section. On a $T s$ diagram show static and stagnation state points and the process path.
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