Engineering, 10.04.2020 00:23 ariellewallenst3393

A rocket motor with a specific impulse (Isp) of 270 seconds is test-fired. The motor is designed with an optimal nozzle that allows full expansion at sea-level. The test verifies that the rocket motor has an average chamber pressure (Pc) of 8.0 MPa. The rocket uses the hypergolic propellants: nitrogen tetroxide (N2O4) and Aerozine 50 [A- 50, a 50/50 mixture of hydrazine (N2H4) and unsymmetrical dimethyl hydrazine (UDMH, C2H3N2)], which produce combustion products that have a ratio of specific heats (y) of 1.3 and a molecular weight (Mw) of 21.3 kg/kmole. The atmospheric pressure at sea-level (Po) is 101.325 kPa. [6x4=24 points] (1) Calculate the ideal thrust coefficient (C:). (2) Calculate the characteristic velocity (C*) in m/s. (3) Determine the effective exhaust velocity (Veff) in m/s. (4) Determine the chamber temperature (Tc) in K.

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A rocket motor with a specific impulse (Isp) of 270 seconds is test-fired. The motor is designed wit...