Surface Flow Visualization of Separated Flows on the Forebody of an F-18 Aircraft and Wind-tunnel Model PDF Download
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Author: David F. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: David F. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Gary E. Erickson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 172
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Author: David F. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 496
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author:
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ISBN:
Category : Science
Languages : en
Pages : 174
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Author: Mark C. Davis
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 68
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Pressure distributions on the wings of the F/A-18A High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing. During quasi-stabilized 1-g flight, data were gathered at ranges for angle of attack from 5 to 70 degrees, for angle of sideslip from -12 to +12 degrees, and for Mach from 0.23 to 0.64, at various engine settings, and with and without the leading edge extension fence installed. Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 to 30 degrees. Influence was seen on the outboard portion of the wing. Angle-of-sideslip influence on wing pressure distribution was strongest at low angle of attack. Influence of Mach number was observed in the regions of local supersonic flow, diminshing as angle of attack was increased. Engine throttle setting had little influence on the wing pressure distribution.
Author:
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Category : Government publications
Languages : en
Pages : 1690
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Author:
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ISBN:
Category : Government publications
Languages : en
Pages : 974
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 172
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