Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720580287
Category :
Languages : en
Pages : 66
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Book Description
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
Author: Mark C. Davis
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 68
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Book Description
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:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1484
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1482
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 458
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 262
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 470
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Book Description
Author: Bruce Larrimer
Publisher:
ISBN: 9781626830592
Category :
Languages : en
Pages :
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Book Description
Author: Douglas A. Joyce
Publisher:
ISBN: 9781626830196
Category : Research aircraft
Languages : en
Pages : 409
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Book Description
The X-31 Enhanced Fighter Maneuverability Demonstrator was unique among experimental aircraft. A joint effort of the United States and Germany, the X-31 was the only X-plane to be designed, manufactured, and flight tested as an international collaboration. It was also the only X-plane to support two separate test programs conducted years apart, one administered largely by NASA and the other by the U.S. Navy, as well as the first X-plane ever to perform at the Paris Air Show. Flying Beyond the Stall begins by describing the government agencies and private-sector industries involved in the X-31 program, the genesis of the supermaneuverability concept and its initial design breakthroughs, design and fabrication of two test airframes, preparation for the X-31's first flight, and the first flights of Ship #1 and Ship #2. Subsequent chapters discuss envelope expansion, handling qualities (especially at high angles of attack), and flight with vectored thrust. The book then turns to the program's move to NASA's Dryden Flight Research Center and actual flight test data. Additional tasking, such as helmet-mounted display evaluations, handling quality studies, aerodynamic parameter estimation, and a "tailless" study are also discussed.The book describes how, in the aftermath of a disastrous accident with Ship #1 in 1995, Ship #2 was prepared for its outstanding participation in the Paris Air Show. The aircraft was then shipped back to Edwards AFB and put into storage until the late 1990s, when it was refurbished for participation in the U. S. Navy's VECTOR program. The book ends with a comprehensive discussion of lessons learned and includes an Appendix containing detailed information.
