Engineering, 20.02.2020 22:39 andrewmena05

During the entry of the Apollo space vehicle into the Earth's atmosphere, the Mach number at a given point on the trajectory was M = 38 and the atmospheric temperature was 270 K. Calculate the temperature at the stagnation point of the vehicle, assuming a calorically perfect gas with γ = 1.4. Do you think this is an accurate calculation? If not, why? If not, is your answer an overestimate or underestimate?

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During the entry of the Apollo space vehicle into the Earth's atmosphere, the Mach number at a given...

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