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Model aerodynamic test results for a refined actuated inlet ejector nozzle at simulated takeoff and cruise conditionsWind tunnel model tests were conducted to demonstrate the aerodynamic performance improvements of a refined actuated inlet ejector nozzle. Models of approximately one-tenth scale were configured to simulate nozzle operation at takeoff, subsonic cruise, transonic cruise and supersonic cruise. Variations of model components provided a performance evaluation of ejector inlet and exit area, forebody boattail angle and ejector inlet operation in the open and closed mode. Approximately 700 data points were acquired at Mach numbers of 0, 0.36, 0.9, 1.2, and 2.0 for a wide range of nozzle flow conditions. Results show that relative to two ejector nozzles previously tested performance was improved significantly at takeoff and subsonic cruise performance, a C sub f of 0.982, was attained equal to the high performance of the previous tests. The established advanced supersonic transport propulsion study performance goals were met or closely approached at takeoff and supersonic cruise.
Document ID
19830018545
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nelson, D. P. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
PWA-5768-29
NAS 1.26:168051
NASA-CR-168051
Accession Number
83N26816
Funding Number(s)
CONTRACT_GRANT: NAS3-22738
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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