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The Effect of Lower Surface Spoilers on the Transonic Trim Change of a Wind-Tunnel Model of a Fighter Airplane Having a Modified Delta WingIn an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter airplane, lower surface spoilers were tested on a 0.055-scale wind-tunnel model. The Mach number range of the tests was 0.8 to 1.2 at Reynolds numbers of approximately 4 million. Although the spoilers produced a moderate decrease in the trim change at low altitudes, they also produced a large increase in drag. Pressure-distribution tests with external fuel tanks showed large pressure changes on the lower surface of the wing due to the tanks.
Document ID
19980228323
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Robinson, Robert C. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1959
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-MEMO-12-27-58A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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