Help me solve this problem A uniform air stream of Ma corner as shown in figure. T stream are 223 K and 25 kPa Unifrom air s М, Т, РP Calculate Mach number downstream the expansion waves 2.6 O 1.8 1 3.9 2.1 O 3.55 2.4 O Calculate the pressure downstream .the expansion wave 17.45 kPa O 2 9.8 kPa O 7.23 КРа 13.38 kPa 6.92 kPa O 11.22 kPa O Calculate the temperature downstream the expansion wave 154.48 K O 3 210.56 K O 130.45 K O 170.66 K O

A jet of alcohol strikes the vertical plates shown in the Figure 2. A force F=425 N is required to hold the plate stationary. Assuming there are no losses in the nozzle, estimate a) The mass flow rate of alcohol. b) The absolute pressure at section 1. P,? Alcohol P.- 101 kPa SG = 0.79 D,S cm

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Thermodynamics/fluid mechanics question is in the image.

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A converging-diverging nozzle with an exit-to-sonic area ratio of Ae/A = 47, exhausts air from a high-pressure reservoir (T, = 270 K) to the back plane, where the pressure is fixed at p, = 1 atm [abs). The test section area is Aa = 0.06 m? and the reservoir has a volume of 50 m. a) Assume that the test is located immediately upstream of the exit and that the flow up to the exit is isentropic, what is the minimum stagnation pressure under which the tunnel will start? b) What is the test section pressure under these conditions?

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