c) When a normal shock wave is in the test section at x = 400 mm, what is the Mach number of the flow ahead of this shock wave? What is the stagnation pressure before and after the shock? 2. You work for an aerospace company which is due to start testing a design in a supersonic wind tunnel. It is a two-dimensional, blow down wind tunnel with rectangular cross-section. The width of the wind tunnel is 100mm and the height at key points is provided in Figure Q2a. At x = 0 mm, the stagnation pressure is always 175 kPa and the stagnation temperature is 300 K. Prior to your test entry, you are given calibration data measured using a Pitot probe mounted in the centre of the test section during wind tunnel start up when the wind tunnel is empty. Your task is to evaluate whether the readings provided by the Pitot probe are sensible to check whether it is working correctly. You can neglect boundary-layer effects throughout this question.
c) When a normal shock wave is in the test section at x = 400 mm, what is the Mach number of the flow ahead of this shock wave? What is the stagnation pressure before and after the shock? 2. You work for an aerospace company which is due to start testing a design in a supersonic wind tunnel. It is a two-dimensional, blow down wind tunnel with rectangular cross-section. The width of the wind tunnel is 100mm and the height at key points is provided in Figure Q2a. At x = 0 mm, the stagnation pressure is always 175 kPa and the stagnation temperature is 300 K. Prior to your test entry, you are given calibration data measured using a Pitot probe mounted in the centre of the test section during wind tunnel start up when the wind tunnel is empty. Your task is to evaluate whether the readings provided by the Pitot probe are sensible to check whether it is working correctly. You can neglect boundary-layer effects throughout this question.
Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
Problem 1RQ
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Transcribed Image Text:c) When a normal shock wave is in the test section at x = 400 mm, what is
the Mach number of the flow ahead of this shock wave? What is the
stagnation pressure before and after the shock?
Transcribed Image Text:2.
You work for an aerospace company which is due to start testing a
design in a supersonic wind tunnel. It is a two-dimensional, blow down
wind tunnel with rectangular cross-section. The width of the wind
tunnel is 100mm and the height at key points is provided in Figure Q2a.
At x = 0 mm, the stagnation pressure is always 175 kPa and the
stagnation temperature is 300 K. Prior to your test entry, you are given
calibration data measured using a Pitot probe mounted in the centre of
the test section during wind tunnel start up when the wind tunnel is
empty. Your task is to evaluate whether the readings provided by the
Pitot probe are sensible to check whether it is working correctly. You can
neglect boundary-layer effects throughout this question.
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