hw5 - tunnel is 10 psia(a Is the tunnel ²ow subsonic of...

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MAE135 Homework No. 5 Spring 2010 Date assigned: Tuesday, April 27, 2010 Due date: 5:00 pm, Tuesday, May 4, 2010 PROBLEM 1 (10 points) p 01 =300 kPa p a = 100 kPa T 01 =300 K 1 2 Combustion chamber Frictionless injector T 01 =300 K Designed assumed T 02 =300 K In reality, T 02 =600 K Air at reservoir conditions of 300 kPa and 300 K is injected into a combustion chamber. For practical reasons the injector is long but can be treated as frictionless. Flow is one dimensional. The engineer designing the injector assumed no heat transfer (i.e., T 0 2 = T 0 1 = 300 K) and calculated that the injector would supply 0.1 kg/sec of air. In reality, the hot combustion environment in the chamber creates signi±cant heat transfer which raises the total temperature of the air at the exit of the injector to T 0 2 = 600 K). Calculate the actual mass ²ow rate of the injector. State clearly, and eventually validate, your assumptions. PROBLEM 2 (10 points) A pitot probe inserted in a wind tunnel reads a pressure of 50 psia. The static pressure in the
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Unformatted text preview: tunnel is 10 psia. (a) Is the tunnel ²ow subsonic of supersonic ? Explain your answer. (b) What is the ²ow Mach number? (c) What is the total pressure of the ²ow in the tunnel? (d) For a reservoir temperature of 300K, assuming adiabatic ²ow, calculate the ²ow velocity in the tunnel. PROBLEM 3 (10 points) A * A 1 p 02 p 01 A normal shock forms inside a convergent-divergent nozzle. We want to develop a relation between the area ratio where the shock sits, A 1 /A * , and the total pressure ratio across the shock, p 2 /p 1 . (this relation cannot be expressed in one equation, but can be described by a set of equations). (a) Describe the procedure and equations you would use to obtain this relation. (b) Plot p 2 /p 1 versus A 1 /A * , with A 1 /A * ranging from 1.0 to 5.0. 1...
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This note was uploaded on 08/31/2010 for the course ENGRMAE 135 taught by Professor Staff during the Spring '08 term at UC Irvine.

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