An Experimental Investigation Of The Expansion Flow Field Over A Delta Wing At Supersonic Speed
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Author | : W. J. Bannink |
Publisher | : |
Total Pages | : 40 |
Release | : 1971 |
Genre | : |
ISBN | : |
Download An Experimental Investigation of the Expansion Flow Field Over a Delta Wing at Supersonic Speed Book in PDF, Epub and Kindle
Author | : Ernest James Cross |
Publisher | : |
Total Pages | : 240 |
Release | : 1968 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download Experimental and analytical investigation of the expansion flow field over a delta wing at hypersonic speeds Book in PDF, Epub and Kindle
Author | : William H. Wentz (Jr.) |
Publisher | : |
Total Pages | : 160 |
Release | : 1966 |
Genre | : Delta wing airplanes |
ISBN | : |
Download An Experimental Investigation of the Flow Fields about Delta and Double-delta Wings at Low Speeds Book in PDF, Epub and Kindle
Author | : Ernest J Cross (Jr) |
Publisher | : |
Total Pages | : 136 |
Release | : 1968 |
Genre | : |
ISBN | : |
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).
Author | : Ernest James Cross (Jr.) |
Publisher | : |
Total Pages | : 0 |
Release | : 1968 |
Genre | : |
ISBN | : |
Download Experimental and Analytical Investigation of the Expansion Flow Field Over a Delta Wing at Hypersonic Speeds Book in PDF, Epub and Kindle
Author | : W.J. Bannink |
Publisher | : |
Total Pages | : |
Release | : 1965 |
Genre | : |
ISBN | : |
Download Investigation on the Flow Field on the Expansion Side of a Delta Wing with Supersonic Leading Edges Book in PDF, Epub and Kindle
Author | : Sharon Rose Donohoe |
Publisher | : |
Total Pages | : 209 |
Release | : 1996 |
Genre | : |
ISBN | : 9789056230364 |
Download Vortex flow and vortex breakdown above a delta wing in high supersonic flow Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 54 |
Release | : 1980 |
Genre | : |
ISBN | : |
Download Leeward Flow Over Delta Wings at Supersonic Speeds Book in PDF, Epub and Kindle
Author | : William H. Wentz |
Publisher | : |
Total Pages | : 129 |
Release | : 1967 |
Genre | : |
ISBN | : |
Download Further Experimental Investigation of Delta and Double-delta Wing Flow Fields at Low Speeds Book in PDF, Epub and Kindle
Author | : Bernard Mazelsky |
Publisher | : |
Total Pages | : 79 |
Release | : 1968 |
Genre | : |
ISBN | : |
Download Research on Hypersonic Flow of Blunt Delta Wings. Part Iii. Gap Effects of a Blunt Slab Delta Wing at Moderate Supersonic and Hypersonic Speeds Book in PDF, Epub and Kindle
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).