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Dynamic ground effects flight test of the NASA F-15 aircraftAerodynamic characteristics of an aircraft may significantly differ when flying close to the ground rather than when flying up and away. Recent research has also determined that dynamic effects (i.e., sink rate) influence ground effects (GE). A ground effects flight test program of the F-15 aircraft was conducted to support the propulsion controlled aircraft (PCA) program at the NASA Dryden Flight Research Center. Flight data was collected for 24 landings on seven test flights. Dynamic ground effects data were obtained for low- and high-sink rates, between 0.8 and 6.5 ft/sec, at two approach speed and flap combinations. These combinations consisted of 150 kt with the flaps down (30 deg deflection) and 170 kt with the flaps up (0 deg deflection), both with the inlet ramps in the full-up position. The aerodynamic coefficients caused by ground effects were estimated from the flight data. These ground effects data were correlated with the aircraft speed, flap setting, and sink rate. Results are compared to previous flight test and wind-tunnel ground effects data for various wings and for complete aircraft.
Document ID
19950026603
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Corda, Stephen (Planning Research Corp. Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1995
Publication Information
Publication: NASA. Dryden Flight Research Center, An Electronic Workshop on the Performance Seeking Control and Propulsion Controlled Aircraft Results of the F-15 Highly Integrated Digital Electronic Control Flight Research Program
Subject Category
Aircraft Design, Testing And Performance
Accession Number
95N33024
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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