Pitot-pressure Distributions of the Flow Field of a Delta-wing Orbiter PDF Download
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 172
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 172
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1280
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Book Description
Author: William H. Wentz (Jr.)
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 160
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Book Description
Author: Scott O. Kjelgaard
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
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Book Description
Author:
Publisher:
ISBN:
Category : Aerothermodynamics
Languages : en
Pages : 470
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Book Description
Author: Marvin Kussoy
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 32
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723082115
Category :
Languages : en
Pages : 130
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Book Description
As part of a cooperative research program between NASA, McDonnell Douglas Corporation, and Wright Research and Development Center, a flow field investigation was conducted on a 7.52 percent scale windtunnel model of an advanced fighter aircraft design. The investigation was conducted in the Langley 16 ft Transonic Tunnel at Mach numbers of 0.6, 0.9, and 1.2. Angle of attack was varied from -4 degrees to 30 degrees and the model was tested at angles of sideslip of 0, 5, and -5 degrees. Data for the over the wing flow field were obtained at four axial survey stations by the use of six 5 hole conical probes mounted on a survey mechanism. The wing leading edge primary vortex exerted the greatest influence in terms of total pressure loss on the over the wing flow field in the area surveyed. A number of vortex control devices were also investigated. They included two different apex flaps, wing leading edge vortex flaps, and small large wing fences. The vortex flap and both apex flaps were beneficial in controlling the wing leading edge primary vortex. Bare, E. Ann and Reubush, David E. and Haddad, Raymond C. Langley Research Center DELTA WINGS; FIGHTER AIRCRAFT; FLOW DISTRIBUTION; SUBSONIC SPEED; TRANSONIC SPEED; VORTEX FLAPS; WIND TUNNEL MODELS; WIND TUNNEL TESTS; ANGLE OF ATTACK; FLOW VISUALIZATION; MACH NUMBER; PRESSURE DISTRIBUTION; SIDESLIP; TRANSONIC WIND TUNNELS...
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 1364
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Book Description
Author: W. H. Wentz
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 140
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Book Description
Author: George C. Ashby
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 28
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Book Description
Elevon hinge moments were determined from measured surface pressures on a typical delta-wing shuttle orbiter model at selective deflection angles for comparison with the extensive experimental and analytical hinge-moment data previously reported for a simple 75 [degrees] delta wing with a trailing-edge control. The angles of attack were from 0 [degrees] to 55 [degrees] at elevondeflection angles of -45.5 [degrees], O [degrees], and 20°. The results show that the elevon hinge moments on the shuttle orbiter are essentially the same as those measured earlier for the more basic model. Also included is an appendix describing a cubic spline function technique used to determine the hinge moments from elevon surface-pressure measurements.
