Engineering, 13.11.2020 16:40 yurionice42069
Consider an ideal turbojet with an afterburner at flight conditions: To = 220 K, P= 20 kPa, and M. = 0.8. Calculate and plot: 1) the specific thrust (T / mdot) versus the afterburner stagnation temperature (T+7) 2) Isp (specific impulse) versus the afterburner stagnation temperature (Tt7) Use the following parameters for your calculations:
T3 = 20, T4 = = 1600 K, and I g = 1600 to 2500 K.
The fuel heat of combustion is hf = 42,800 kJ/kg and the properties of air are: y = 1.4, R = 287J/kg-K, and Cp = 1005 J/kg-K.
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Consider an ideal turbojet with an afterburner at flight conditions: To = 220 K, P= 20 kPa, and M. =...
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