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Engineering, 09.02.2021 05:40 21megoplin

At a given point in the high-speed flow over an airplane wing, the local Mach number, pressure and temperature are 0.7,0.9 atm, and 250 K, respectively. Calculate the values of p,, To, p*, T*, and a* at this point.

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At a given point in the high-speed flow over an airplane wing, the local Mach number, pressure and t...
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