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In Flight Wing Pressure Distributions For The Nasa F A 18a High Alpha Research Vehicle
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Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723851636 Total Pages :68 pages Book Rating :4.8/5 (516 download)
Book Synopsis In-Flight Wing Pressure Distributions for the NASA F/A-18a High Alpha Research Vehicle by : National Aeronautics and Space Adm Nasa
Download or read book In-Flight Wing Pressure Distributions for the NASA F/A-18a High Alpha Research Vehicle written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-20 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 deg to 70 deg, for angle of sideslip from -12 deg to +12 deg, 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 deg to 30 deg. 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.Davis, Mark C. and Saltzman, John A.Armstrong Flight Research CenterWINGS; PRESSURE DISTRIBUTION; WIND TUNNEL TESTS; F-18 AIRCRAFT; RESEARCH VEHICLES; LIFT; ORIFICES; SUPERSONIC FLOW; BOUNDARY LAYER SEPARATION; DATA REDUCTION; COMPUTATIONAL FLUID DYNAMICS; PIPES (TUBES); FLOW VISUALIZATION; FLIGHT TESTS; ANGLE OF ATTACK
Book Synopsis In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle by : Mark C. Davis
Download or read book In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle written by Mark C. Davis and published by . This book was released on 2000 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
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