An Experimental Investigation of the Expansion Flow Field Over a Delta Wing at Supersonic Speed PDF Download
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Author: W. J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Book Description
Author: W. J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Author: Ernest James Cross
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 240
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Author: William H. Wentz (Jr.)
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 160
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Author: Ernest J Cross (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 136
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An experimental and analytical investigation was carried out to determine the character of the lee side flow field over a slender delta wing with sharp leading edges in a hypersonic free stream. The experiments of the initial phase of a two part experimental program were for the purpose of obtaining qualitative data to identify the dominant features of the flow field. Schlieren, vapor screen and surface oil flow were useful experimental techniques in this application. The surface pressure, surface temperature, and impact pressure were measured at the points of an extensive array in the lee side flow to determine the magnitude and extent of the flow phenomena. Analysis of the experimental results led to a description of the principal features of the flow field. The character of the flow was identified in three regimes by a specific and dominant property of the flow. The principal concern of this research program was for regime number 2 which had the following characteristics. The viscous flow field on the lee side of the wing caused a significant interaction with the inviscid flow which caused an effective change in the wing geometry. The flow expanded to the displacement boundary layer across the wing leading edge, causing a deflection of the velocity vector toward the plane of symmetry (a plane through the central chord and normal to the surface of the wing), which caused the occurrence of a realignment shock imbedded in the inviscid flow. This shock was sufficiently strong to cause the viscous layer to separate. Results of an impact pressure survey indicated that to a good approximation, the flow field was conical. (Author).
Author: Ernest James Cross (Jr.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Author: W.J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Sharon Rose Donohoe
Publisher:
ISBN: 9789056230364
Category :
Languages : en
Pages : 209
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
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Author: William H. Wentz
Publisher:
ISBN:
Category :
Languages : en
Pages : 129
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Author: Bernard Mazelsky
Publisher:
ISBN:
Category :
Languages : en
Pages : 79
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An experimental investigation of the effect of air ejecting from the windward side to the leeward side through gaps located on a delta wing on the aerodynamic performance was made at hypersonic speeds, M = 6 and 10, and at three Reynolds numbers, Re/ft = 1,500,000, 1,600,000 and 3,800,000. The tested data and the oil flow photographs indicate that the gap effect has a negligible influence on the lift and drag of the wing at the tested Mach numbers and Reynolds numbers. The model used in these tests was the same as that used for the previous experiment (Part II) wherein the gap width varied from 0.015 inch to 0.045 inch. In addition to the measurement of lift and drag, velocity profiles, surface pressures and base pressures were also measured in the present experiment. (Author).
