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where v_2 - v_1 = v_2 * cos(Lambdaλ)
where c_p = 1004.5 for air and Lambda is the sweep angle of the fins
Assuming the rocket reaches a target of 30K ft AGL:
T_static = 59F - .00356(F/ft) * 30000 h_{max_v} (ft) = -47.8 F = 228.82 K
Therefore,
T_stag = 228.82 K + (59F - .00356(F/ft) * h_{max_v} (ft)) + (4.9776008*10^{-4}) * (v_2 * cos(Lambdaλ))^2
v_2 = Mach 2 = 2*343 (m/s) = 686 (m/s)
T_stag = 228.82 K (59F - .00356(F/ft) * h_{max_v} (ft)) + (4.9776008*10^{-4}) * (686 (m/s) * cos(Lambdaλ))^2
Dynamic Pressure
Dynamic pressure (q) represents the aerodynamic pressure exerted on a vehicle in motion through a fluid (air). It is defined by the equation:
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