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An experimental investigation of dynamic ground effectSixty degree delta wing, F-106B, and XB-70 models with and without flap deflections were tested in static and dynamic ground effect in the 36 by 51 inch subsonic wind tunnel at the University of Kansas. Dynamic ground effect was measured with movable sting support. For flow visualization, a tufted wire grid was mounted on the movable sting behind the model. Tests results showed that the lift and drag increments in dynamic ground effect were always lower than the static values. Effect of the trailing-edge flap deflections on lift increments was slight. The fuselage reduced the lift increments at a given ground height. From flow visualization under static conditions, the vortex core was seen to enlarge as the ground approached.
Document ID
19870016603
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lee, Pai Hung (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Lan, C. Edward (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Muirhead, Vincent U. (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1987
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-180560
NAS 1.26:180560
CRINC-FRL-717-1
Accession Number
87N26036
Funding Number(s)
CONTRACT_GRANT: NAG1-616
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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