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Engineering, 26.02.2020 03:56 onlyceleste2430

At a given point in the high-speed flow over an airplane wing, the local Machnumber, static pressure, and static temperature are 0.7, 0.9 atm, and 250 K, respectively. Calculate the total pressure, total temperature at this point.

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At a given point in the high-speed flow over an airplane wing, the local Machnumber, static pressure...
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