A supersonic wind tunnel is in the design stage. It is to be driven by a large upstream reservoir of compressed air and discharges to atmospheric conditions downstream. Thetest section has a constant cross-sectional area and lies downstream of a throat, which is a converging-diverging section that serves to accelerate the flow to supersonicconditions. For the duration of any given experiment, the reservoir can be considered to have constant stagnation conditions that are To = 313K and po = 6x105 Pa. The specificgas constant R = 287J kg-1 K-1 and the specific heat ratio is y = 1.4.The wind tunnel test section is designed to run with a cross-sectional area A (test section ) = 1.2 m² and Mach number M (test section ) = 3.5.Find the area of the throat that lies between the reservoir and the test section. Give your answer in m² to two decimal places.

given P0=6*105PaT0=313 KA1=1.2 m2M1=3.5 AA*=1M2γ+11+γ-12M2.5γ+1γ-1

Answered: A supersonic wind tunnel is in the…

Engineering

Mechanical Engineering

A supersonic wind tunnel is in the design

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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