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Calculate Specific Impulse, Mass Flow, Exit Velocity, Thrust of Rocket Engine at Standard Altitude Method to Calculate the Specific Impulse, Mass Flow, Exit Velocity, Mach Number at Exit, Thrust of the Rocket Engine at a Standard Altitude 

Aerospace



Thrust, Specific Impulse, Exit Velocity, Mass Flow of a Rocket Engine at a Standard Altitude In this topic we would look into how to calculate the thrust of a Rocket Engine at a Standard Altitude above the surface of Earth. 

The parameters we require are, The Combustion Chamber Pressure of Rocket in atm. The Combustion Chamber Temperature Rocket in Kelvin K.
Rocket Nozzle Throat and Rocket Nozzle Exit Areas. Note: In the calculations we assume that the rocket is designed in such a way that the exit pressure = ambient pressure.
We would also require the Altitude where the rocket is flying in meters (m). The value of gamma for the gas mixture The value of the Molecular Weight M The value of the Universal Gas Constant used in the calculation is R = 8314 J/(kg mol)K Acceleration due to Gravity, g = 9.8 m/sec^2


Performing the calculation, gives us,
Download Free Program to Calculate the Thrust of the Rocket Engine at Standard Altitude.

