Preliminary Measurements of the Flow Field on the Leeside of a Delta Wing of Unit Aspect Ratio at a Mach Number of 2.6 and an Incidence of 15 Degrees PDF Download
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Author: L. Gaudet
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Category :
Languages : en
Pages :
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Author: L. Gaudet
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
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ISBN:
Category :
Languages : en
Pages : 54
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Category : Airplanes
Languages : en
Pages : 44
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Author: Robert S. Osborne
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Category : Aerodynamics
Languages : en
Pages : 20
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 59
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A procedure is developed which utilizes the method of characteristics to solve a portion of the flow field on the lee side of a flat plate delta wing with supersonic leading edges at angle of attack but at zero yaw. The procedure requires input conditions of a free stream Mach number an angle of attack and a sweep angle. The procedure is applied to three sets of input conditions and the resulting data are compared to published experimental and analytical data for the same set of input conditions. The comparisons indicate that the procedure may be useful in predicting the flow field in the pseudo-elliptic region and the position of the internal shock wave on the lee side of the wing.
Author: Frank J. Centolanzi
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Category : Mach number
Languages : en
Pages : 82
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Author: Frederick C. Grant
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Category : Mach number
Languages : en
Pages : 46
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Author: W. H. Wentz
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Category : Aerodynamic load
Languages : en
Pages : 140
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Author: Raymond E. Gordnier
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Category : Airplanes
Languages : en
Pages : 38
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A numerical investigation of the flow field about a 76-degree leading edge sweep delta wing at 20.5 degree angle of attack is presented. The computational results are obtained using a Beam-Warming algorithm with a Newton-like subiteration procedure. For M = 0.2 and Re = 900,000 an unsteady flow field is obtained which is shown to be physical in nature. The unsteady behaviour is a result of the existence of small-scale vortical structures that are associated with a Kelvin-Helmholtz type instability of the shear layer emanating form the leading edge of the delta wing. The computed results show qualitative agreement with other experimental and numerical findings.
Author: E. Ann Bare
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ISBN:
Category :
Languages : en
Pages : 146
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