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H=9144;//standard altitude at which airplane flying(meter)
P=0.3014*10^5;//pressure at standard altitude of 9144 m(N/m^2)
D=0.459;//Density at standard altitude of 9144 m(Kg/m^3)
V=804.67*5/18 //free stream velocity(m/s)
Pe=0.3064*10^5;//pressure of exhaust gas at the exit(N/m^2)
Ve=487.68;//velocity of exhaust gas at exit(m/s)
Ai=0.65;//inlet area(m^2)
Ae=0.42;//exit area(m^2)
Mdot=D*V*Ai //mass flow through engine(Kg/s)
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