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Comparison of theoretical and flight-measured local flow aerodynamics for a low-aspect-ratio finFlight test and theoretical aerodynamic data were obtained for a flight test fixture mounted on the underside of an F-104G aircraft. The theoretical data were generated using two codes: a two-dimensional transonic code called code H, and a three-dimensional subsonic and supersonic code called wing-body. Pressure distributions generated by the codes for the flight test fixture, as well as compared with the flight-measured data. The two-dimensional code pressure distributions compared well except at the minimum pressure point and the trailing edge. Shock locations compared well except at high transonic speeds. However, the two-dimensional code did not adequately predict the displacement thickness of the flight test fixture. The three-dimensional code pressure distributions compared well except at the trailing edge of the flight test fixture.
Document ID
19870006508
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Johnson, J. Blair (NASA Ames Research Center Moffett Field, CA, United States)
Sandlin, Doral R. (California Polytechnic State Univ. San Luis Obispo, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-86806
NAS 1.15:86806
H-1336
Accession Number
87N15941
Funding Number(s)
PROJECT: RTOP 505-60-21
CONTRACT_GRANT: NCC4-1
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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