Experimental Study Of Supersonic Viscous Leeside Flow Over A Slender Delta Wing
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Total Pages | : 74 |
Release | : 1980 |
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Download Experimental Study of Supersonic Viscous Leeside Flow Over a Slender Delta Wing Book in PDF, Epub and Kindle
Author | : I.C. Richards |
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Total Pages | : 6 |
Release | : 1975 |
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Download Supersonic Flow Past a Slender Delta Wing Book in PDF, Epub and Kindle
Author | : Ernest J Cross (Jr) |
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Total Pages | : 136 |
Release | : 1968 |
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Download Experimental and Analytical Investigation of the Expansion Flow Field Over a Delta Wing at Hypersonic Speeds Book in PDF, Epub and Kindle
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).
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Total Pages | : 54 |
Release | : 1980 |
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Download Leeward Flow Over Delta Wings at Supersonic Speeds Book in PDF, Epub and Kindle
Author | : David S. Miller |
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Total Pages | : 160 |
Release | : 1985 |
Genre | : Aerodynamics, Supersonic |
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Download Lee-side Flow Over Delta Wings at Supersonic Speeds Book in PDF, Epub and Kindle
Author | : Susan Naomi McMillin |
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Total Pages | : 108 |
Release | : 1990 |
Genre | : Aerodynamics, Supersonic |
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Download Navier-Stokes and Euler Solutions for Lee-side Flows Over Supersonic Delta Wings Book in PDF, Epub and Kindle
Author | : |
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Total Pages | : 1572 |
Release | : 1992 |
Genre | : Aeronautics |
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Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle
Author | : Y. C. Vigneron |
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Total Pages | : 86 |
Release | : 1978 |
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Download Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges Book in PDF, Epub and Kindle
Author | : Bernard Mazelsky |
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Total Pages | : 82 |
Release | : 1967 |
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Download Research on Hypersonic Flow of Blunt Delta Wings. Part I. Theoretical and Experimental Study of a 70-degree Blunt Delta Wing for Low Angles of Attack at Supersonic and Hypersonic Speeds Book in PDF, Epub and Kindle
The object of the present analysis is to investigate the high-speed aerodynamic properties of a blunt delta wing at low angles of attack where the maximum lift to drag ratio occurs. Oguchi's solution of hypersonic flow over a blunt leading edge flat plate at zero incidence is extended to three dimensional delta wings at angle of attack. The shock wave shapes and pressure distributions were obtained by employing the oblique shock relations at the windward sides of the Prandtl-Meyer equations at the leeward side of the wing. The total lift and drag of the wing due to pressure and skin friction were computed by numerical integration using the IBM 7094 computer. The present calculated aerodynamic forces generally agree with the experimental data at the high supersonic Mach numbers (M approx.> or = 4) and lower thickness ratio of the wing which is a 70-degree swept slab sided delta wing with a cylindrical leading edge. (Author).
Author | : Richard M. Wood |
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Total Pages | : 220 |
Release | : 1987 |
Genre | : Aerodynamics, Supersonic |
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Download Study of Lee-side Flows Over Conically Cambered Delta Wings at Supersonic Speeds Book in PDF, Epub and Kindle