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Book Supersonic Flow Past a Slender Delta Wing

Download or read book Supersonic Flow Past a Slender Delta Wing written by I.C. Richards and published by . This book was released on 1975 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Experimental and Analytical Investigation of the Expansion Flow Field Over a Delta Wing at Hypersonic Speeds

Download or read book Experimental and Analytical Investigation of the Expansion Flow Field Over a Delta Wing at Hypersonic Speeds written by Ernest J Cross (Jr) and published by . This book was released on 1968 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

Book Leeward Flow Over Delta Wings at Supersonic Speeds

Download or read book Leeward Flow Over Delta Wings at Supersonic Speeds written by and published by . This book was released on 1980 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Lee side Flow Over Delta Wings at Supersonic Speeds

Download or read book Lee side Flow Over Delta Wings at Supersonic Speeds written by David S. Miller and published by . This book was released on 1985 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book 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

Download or read book 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 written by Bernard Mazelsky and published by . This book was released on 1967 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

Book NASA Technical Paper

Download or read book NASA Technical Paper written by and published by . This book was released on 1990 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Aeronautical Engineering

Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Applied Mechanics Reviews

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1979 with total page 556 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Lee side Flow Over Delta Wings at Supersonic Speeds

Download or read book Lee side Flow Over Delta Wings at Supersonic Speeds written by David S. Miller and published by . This book was released on 1985 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: