On The Hypersonic Flow Past Blunted Flat Delta Wings
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| Author | : Arnold Polak |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1970 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
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).
| Author | : Arnold Polak |
| Publisher | : |
| Total Pages | : 23 |
| Release | : 1970 |
| Genre | : |
| ISBN | : |
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).
| Author | : Norman D. Malmuth |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1965 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges Book in PDF, Epub and Kindle
| Author | : Bernard Mazelsky |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1968 |
| Genre | : |
| ISBN | : |
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).
| Author | : Joseph L. Francis |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1966 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download Hypersonic Flow Over Delta Wings at High Angles of Attack Book in PDF, Epub and Kindle
| Author | : Bernard Mazelsky |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1967 |
| Genre | : |
| ISBN | : |
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 | : |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1967 |
| Genre | : |
| ISBN | : |
Download Research on Hypersonic Flow of Blunt Delta Wings Book in PDF, Epub and Kindle
| Author | : Alexander B. Lessin |
| Publisher | : |
| Total Pages | : |
| Release | : 1993 |
| Genre | : |
| ISBN | : |
Download Abnormal Peaks of Increased Heat-transfer on the Blunted Delta Wing in the Hypersonic Flow Book in PDF, Epub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1966 |
| Genre | : |
| ISBN | : |
Download Research on Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack 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).
