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Axisymmetric & non-axisymmetric exhaust jet induced-effects on a V/STOL vehicle design. Part 1: Data presentationA 1/8 scale jet-effects model was tested in the NASA Ames 11 ft transonic tunnel at static conditions and over a range of Mach numbers from 0.4 to 1.4. The data presented show that significant differences in aeropropulsion performance can be expected by varying the exhaust nozzle type and its geometric parameters on a V/STOL underwing nacelle installation.
Document ID
19810016529
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Schnell, W. C. (Grumman Aerospace Corp. Bethpage, NY, United States)
Ordonez, G. W. (Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1981
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-166146
REPT-0747-81-PT-1
Report Number: NASA-CR-166146
Report Number: REPT-0747-81-PT-1
Accession Number
81N25064
Funding Number(s)
PROJECT: RTOP 505-42-71
CONTRACT_GRANT: NAS2-9887
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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