The computer program 'HPROP' has been completed to calculate the parameters of thrust performance of rocket engines on the basis of the Brinkley and G1assman methods. The program can afford to calculate the flame temperature, product composition etc. from the thermodynamical equilibrium relationships without any assumption of the specific heat ratio. The calculation of one-dimensional non-equilibrium expansion flow with chemical kinetics in rocket nozzle 'NOZFLA' also is programmed, based on the Zucrow's method. Further, the program 'CONDY' based on the Svehla's method can calculate the thermal conductivity of combustion gases in which the effect of incomplete combustion or partially frozen flow can be taken into account. The results calculated with this program explain successfully the experimental results of the tests HST-70l, HST-1001 and TC-1002 concerning the increase in the temperature of the coolant through the regenerative cooling passage and the efficiency of the characteristic exhaust velocity.
理論性能計算
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