Maurice Tutor

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    Argosy University/ Phoniex University/
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Category > Engineering Posted 14 May 2018 My Price 3.00

supersonic wind

8.1     The temperature in the reservoir of a supersonic wind tunnel is 519◦R. In the test section, the flow velocity is 1385 ft/s. Calculate the test-section Mach number. Assume the tunnel flow is adiabatic.

8.2     Consider the isentropic flow over an airfoil. The freestream conditions correspond to a standard altitude of 10,000 ft and M∞ = 0.82. At a given point on the airfoil, M = 1.0. Calculate p and T at this point. (Note: You will have to use the standard atmosphere table in Appendix E for this

problem.)

 

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Maurice Tutor
(5)
Status NEW Posted 14 May 2018 02:05 PM My Price 3.00

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