Test 2 MAE356

Test 2 MAE356 - Practice Test 2: Exam will cover: from Area...

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Practice Test 2: Exam will cover: from Area change through shock interactions Will not cover: expansion waves One multipart short answer Three calculator type problems - Nozzles - Diffusers - Oblique shocks - Shock interactions - Shock interactions with walls 1. (T2.1) a. Sketch a Mach reflection and describe the condition at which it will occur. b. Describe the ‘jump’ conditions across the slip line. c. A wind-tunnel is designed for a test section Mach number of 4.0. What is the smallest ratio of the diffuser throat area that will enable the tunnel to start. 2. (T2.2) Consider the airfoil shape shown below. a. Derive the equation for the lift coefficient. b. Calculate the lift coefficient using shock/expansion theory 3. (T2.3) A supersonic wind-tunnel is designed for a test section Mach number of 3.0. Given that the nozzle throat area is 0.1 m 2 , the reservoir stagnation pressure is 20 atm, and the diffuser exit area is 0.59 m 2 and assuming that the diffuser is properly designed and the tunnel is started. a. Find the diffuser Mach number. b. Find the back pressure required to stabilize the terminating shock exactly at the diffuser throat. c. At what back pressure would the terminating shock sit exactly at the diffuser exit? 4. (T2.4) Consider the picture below. a. Find the angle so that the reflected shock just touches the leading edge of the flat plate. b. Find the Mach number and the flow direction (relative to the horizontal) in Region 4.
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5. (H.6.1) Air flows isentropically at a rate of 0.5 kg/s through a converging-diverging nozzle. At the inlet, the pressure is 650 kPa, the temperature is 285 K, and the area is 0.00065 m 2 . If the exit area is 0.0013 m
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Test 2 MAE356 - Practice Test 2: Exam will cover: from Area...

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