A turbojet engine is desired for powering supersonic interceptor. Here analyses is conducted to examine the ideal engine performance. The objective of this project is to determine the variation of performance curves with the design parameters and flight conditions. Default values chosen:
Flight Mach Number (M0): 2
Turbine stagnation temperature ratio λ τ : 7
Atmospheric air temperature: 222.2 K
cp =1004.9 J /(K kg)
hPR = 4.4194*10 J/kg
γ =1.4
hPR = 4.4194×107 J/kg
γ = 1.4
In the first question the given conditions were kept all other parameters as constant but varied compressor ratio ( pic ) was varied from 5 to 60 to calculate specific thrust, thrust specific fuel consumption. In the second question the given conditions were kept all other parameters as constant but varied the Mach no from 0.1 to 2.5 to calculate specific thrust, thrust specific fuel consumption. In the third question the given conditions were kept all other parameters as constant but varied the taulamda from 5 to 12 to calculate specific thrust, thrust specific fuel consumption.