Aerospace Engineering > GATE 2012 > Rocket Propulsion
A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. The universal gas constant is 8314 J/kg-mole-K. The value of theoretical c*(in m/s) is
Correct : 1341 to 1343
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