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F-15 SMTD low speed jet effects wind tunnel test resultsKey results from low speed wind tunnel testing of the F-15 STOL and Maneuver Technology Demonstrator (SMDT) with thrust reversers are presented. Longitudinally, the largest induced increments in the stability and control occur at landing gear height. These generally reflect an induced lift loss and a nose-up pitching moment, and vary with sideslip. Directional stability is reduced at landing gear height with full reverse thrust. Nonlinearities in the horizontal tail effectiveness are found in free air and at landing gear height.
Document ID
19890001482
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Blake, William B. (Air Force Wright Aeronautical Labs. Wright-Patterson AFB, OH, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1988
Publication Information
Publication: NASA, Ames Research Center, The 1987 Ground Vortex Workshop
Subject Category
Aerodynamics
Accession Number
89N10853
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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