The performance of an airframe-integrated scramjet engine is calculated using a quasi-one-dimensional model. The forebody of the airframe is approximated as a cone. Experimental data correlations are used to estimate pressure recovery and capture area of the inlet. Assuming mixing controlled combustion, NASA's empirical relation for fuel mixing efficiency is employed to give the corresponding combustion efficiency distribution. The calculated results serve as engine data for a flight analysis of a space plane. The analysis is being extended to analyze overall engine cycles including subsystems for engine/airframe cooling and fuel supply.
Calculation of Scramjet Performance
1988
33 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Combustion efficiency , Propulsion system performance , Propulsion system configurations , Supersonic combustion ramjet engines , Aerospace planes , Engine airframe integration , Inlet flow , Pressure recovery , Spacecraft propulsion , Foreign technology , Scramjet engines , Mathematical models
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