Computational Analysis of Integrated Engine Exhaust Nozzle on a Supersonic Fighter Aircraft

A unique approach of analyzing jet exhaust nozzle integrated to aircraft and propulsion system is presented in this paper. Engine exhaust nozzle is usually omitted in Wind Tunnel Testing and numerical analysis of aircraft due to complexities involved in integration of nozzle and presence of high pre...

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Veröffentlicht in:	Journal of Applied Fluid Mechanics 2018-11, Vol.11 (6), p.1511-1520
Hauptverfasser:	Arif, I., Masud, J., Shah, S.
Format:	Artikel
Sprache:	eng
Schlagworte:	Aerodynamics Aerodynamics Internal Flows Nozzle Plume Nozzle Pressure Ratio Airborne observation Aircraft Aircraft performance Airframes Computational fluid dynamics Computer applications Exhaust emissions Exhaust nozzles Exhaust systems Fighter aircraft Flow characteristics Flow distortion Fuselages High pressure Inlet temperature Integration Jet exhaust Military aircraft Nozzle flow Numerical analysis Parameters Pressure Pressure ratio Propulsion systems Stabilizers (fluid dynamics) Supersonic aircraft Temperature ratio Turbulence Turbulent flow Wind tunnel testing Wind tunnels
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