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
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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 | : Bernard Mazelsky |
Publisher | : |
Total Pages | : 62 |
Release | : 1966 |
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Download Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack. I. Shock Wave Shape and Surface Pressure Distribution Book in PDF, Epub and Kindle
This report covers a portion of a research program on the aerodynamic characteristics of a cylindrical-leading-edge 70 degrees swept delta wing at high supersonic and moderate hypersonic Mach numbers, and for small values of angle of attack. Prior to the calculation of the lift and drag characteristics of the wing, a semi-empirical method was developed to predict the shock wave shape surrounding the wing as well as the corresponding pressure distribution on the wing surface. The theoretical shock shape and pressure distribution results are compared with experiments available from the open literature as well as with experimental pressure distributions obtained in the present program on the tip portion of a blunt 70 degrees swept delta wing. Within the range of applicability of the semi-empirical method, the predicted shock wave shapes are in good agreement with experiment. The calculated pressure distributions agree quite well with experiment, provided the angle of attack is below 15 degrees and the Mach number is above M = 3.0.
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Total Pages | : 1264 |
Release | : 1967 |
Genre | : Aeronautics |
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Download OAR Cumulative Index of Research Results Book in PDF, Epub and Kindle
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Total Pages | : 1134 |
Release | : 1989 |
Genre | : Aeronautics |
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Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle
Author | : Mitchel H. Bertram |
Publisher | : |
Total Pages | : 136 |
Release | : 1963 |
Genre | : Aerodynamics, Hypersonic |
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Download An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow Book in PDF, Epub and Kindle
Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Author | : Bernard Mazelsky |
Publisher | : |
Total Pages | : 79 |
Release | : 1968 |
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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).
Author | : Arnold Polak |
Publisher | : |
Total Pages | : 48 |
Release | : 1970 |
Genre | : Aerodynamics, Hypersonic |
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Download On the Hypersonic Flow Past Blunted, Flat Delta Wings Book in PDF, Epub and Kindle
The flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author).
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Total Pages | : 56 |
Release | : 1966 |
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Download Research on Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 840 |
Release | : 1968 |
Genre | : Science |
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Download U.S. Government Research & Development Reports Book in PDF, Epub and Kindle
Author | : Bernard Mazelsky |
Publisher | : |
Total Pages | : 86 |
Release | : 1968 |
Genre | : |
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Download Research on Hypersonic Flow of Blunt Delta Wings. Part Ii. Gap Effects of a Blunt Slab Delta Wing at Moderate Supersonic and Hypersonic Speeds Book in PDF, Epub and Kindle
It was found that the maximum lift to drag ratio of a flat delta wing at moderate supersonic and hypersonic speeds can be increased appreciably by letting a small amount of air pass through narrow gaps located at proper places on the wing. The increase in (L/D)max obtained from such a wing experiment varies from 5% to 17% at different speeds. Six gap configurations were tested at four different free stream Mach numbers, M = 4, 4.5, 5 and 8. Reynold's number was kept constant at Re/in = 300,000 and 700,000. Both the lift and drag of the wing were reduced due to the presence of gaps. Since the decrease in drag is greater than that of lift, L/D is thus increased. The reduction in lift is due to the loss of momentum and the increase of pressure in the induced separation region on the leeward side of the wing; the reduction in drag is due to the decrease in skin-friction caused by gap effects. (Author).