Item Details

Pressures and Temperatures on the Lower Surfaces of an Externally Blown Flap System During Full-Scale Ground Tests

by Donald L. Hughes
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973.
Language
English
Series
NASA Technical Note
Summary
Full-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
Description
32 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
Prepared at the NASA Flight Research Center.
Series Statement
NASA technical note ; NASA TN D-7138
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Hughes, Donald L. q| (Donald Lee), d| 1926-
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    a| Pressures and temperatures on the lower surfaces of an externally blown flap system during full-scale ground tests c| by Donald L. Hughes.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1973.
    300
      
      
    a| 32 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| NASA TN D-7138
    500
      
      
    a| Prepared at the NASA Flight Research Center.
    520
      
      
    a| Full-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,
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Aerodynamic load x| Measurement.
    650
      
    0
    a| Flaps (Airplanes) x| Testing.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
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    a| Flight Research Center (U.S.)
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106885178 y| 1973 r| pd q| bib

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