Experimental results from a wind tunnel test conducted to investigate propulsion/airframe integration (PAI) effects are presented. The objectives of the test were to examine rough order-of-magnitude changes in the acoustic characteristics of a mixer/ejector nozzle due to the presence of a wing and to obtain limited wing and nozzle flow-field measurements. A simple representative supersonic transport wing planform, with deflecting flaps, was installed above a two-dimensional mixer/ejector nozzle that was supplied with high-pressure heated air. Various configurations and wing positions with respect to the nozzle were studied. Because of hardware problems, no acoustics and only a limited set of flow-field data were obtained. For most hardware configurations tested, no significant propulsion/airframe integration effects were identified. Significant effects were seen for extreme flap deflections. The combination of the exploratory nature of the test and the limited flow-field instrumentation made it impossible to identify definitive propulsion/airframe integration effects.
Experimental Investigation of Wing Installation Effects on a Two-Dimensional Mixer/Ejector Nozzle for Supersonic Transport Aircraft
1992
31 pages
Report
No indication
English
Aerodynamics , Aircraft , Acoustic properties , Ejectors , Engine airframe integration , Exhaust nozzles , Flow distribution , Inlet flow , Noise reduction , Nozzle flow , Supersonic transports , Wind tunnel tests , Wings , High temperature air , Jet aircraft noise , Jet mixing flow , Nozzle design , Pressure distribution
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