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타이틀	IN-FLIGHT WING PRESSURE DISTRIBUTIONS FOR THE NASA F/A-18A HIGH ALPHARESEARCH VEHICLE
저자	Mark C. Davis and John A. Saltzman
Keyword	F-18; Flight test; Flow visualization; Lift; Pressure distribution; Separation; Wingpressures
URL	http://www.dfrc.nasa.gov/DTRS/2000/PDF/H-2389.pdf
보고서번호	NASA-TM-2000-209018
발행년도	2000
출처	NASA Dryden Flight Research Center
ABSTRACT	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 degrees to 70 degrees, for angle of sideslip from ?2 degrees 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 degrees to 30 degrees. Influence by the leading edge extension fence was evident on the inboard wing pressure distribution, but little 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, diminishing as angle of attack was increased. Engine throttle setting had little influence on the wing pressure distribution.