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Experimental investigation of wing installation effects on a two-dimensional mixer/ejector nozzle for supersonic transport aircraftExperimental 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.
Document ID
19960000325
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Anderson, David J. (NASA Lewis Research Center Cleveland, OH, United States)
Lambert, Heather H. (NASA Lewis Research Center Cleveland, OH, United States)
Mizukami, Masashi (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
E-7107
NASA-TM-105713
NAS 1.15:105713
Accession Number
96N10325
Funding Number(s)
PROJECT: RTOP 537-02-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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