>>10880822lol
M = Mach number
R = gas constant of air
Gamma = specific heats of air (1.4)
T = absolute temperature of air
P = pressure of air
A= cross sectional area
the resource said the mass flow rate of the exit is approximately equal to the mass flow rate of the inlet, which is the mass flow rate of the free stream entering, since little fuel is added when the air is compressed
So to find mass flow rate,
m = (rho)(A)(v) = (P/RT)Av
Then using mach number = (speed of stream)/local speed of sound
local speed of sound = sqrt(gammaRT)
sorry I don’t know how to type the equations on here
And yes, I thought it was geometry dependent so that’s why I wanted someone to look at this equation
