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Survey of wing and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap systemFull-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
Document ID
19730024214
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hughes, D. L.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1972
Publication Information
Publication: STOL Technol.
Subject Category
Aerodynamics
Accession Number
73N32947
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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