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 Calculate Pressure in Combustion Chamber of Rocket Engine

 Method to Compute the Pressure in the Combustion Chamber of a Rocket Engine 





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Pressure in Combustion Chamber Rocket Engine/Motor

In order to calculate the pressure in the combustion chamber of a rocket engine we must have the value of the mass flow in lbm/sec.



Furthermore, the value of the Temperature, T0 is required in degree Rankine.


The default value of R used in the calculation is,

R = 2400

and the Value of the gamma = 1.21


We also require to input the Throat Area of Rocket Engine, A* in ft^2.


Performing the calculation gives us the value of the Pressure in the Combustion Chamber, P0

Download Free Program to Calculate the Pressure in the combustion chamber of rocket engine