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Pressures and temperatures on the lower surfaces of an externally blown flap system during full-scale ground testsFull-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 levels and engine/wing positions. The test were made with no airflow over the wing. The wing sweep angle was fixed at e6 deg; and the angle of incidence between the engine and the wing was fixed at 3 deg; and the flap was in the retracted, deflected 35 deg, and deflected 60 deg positions. The pressure load obtained by integrating the local pressures on the undersurface of the flap, F sub p was approximately three times greater at the 60 deg flap position than at the 35 deg flap position. At the 60 deg flap position, F sub p was between 40 percent and 55 percent of the engine thrust over the measured range of thrust. More than 90 percent of F sub p was contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline with both nozzle configurations. Maximum temperatures recorded on the flaps were 218 C (424 F) and 180 C (356 F) for the conical and daisy nozzles, repectively,
Document ID
19730006257
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Hughes, D. L. (NASA Flight Research Center Edwards, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-7138
H-729
Accession Number
73N14984
Funding Number(s)
PROJECT: RTOP 741-72-09-00-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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