Engineering, 05.11.2020 18:40, sean7900

Consider an ideal turbojet with an afterburner at flight conditions: To = 220 K, P= 20 kPa, and M. = 0.8. Calculate and plot: a. the specific thrust
b. Isp versus the afterburner stagnation temperature (Tt7).

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Consider an ideal turbojet with an afterburner at flight conditions: To = 220 K, P= 20 kPa, and M. =...