A ramjet has a constant-diameter combustion chamber followed by a nozzle whose throat diameter is 0.94 times the chamber diameter. Air enters the combustion chamber with T0 = 1450 K and M = 0.3. How high may the temperature rise in the combustion chamber without necessarily changing the chamber inlet conditions? For simplicity, neglect frictional losses in the chamber and nozzles and assume that the working fluid has specific heat ratio γ = 1.333.
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