On The Hypersonic Flow Past Blunted Flat Delta Wings
Download On The Hypersonic Flow Past Blunted Flat Delta Wings full books in PDF, epub, and Kindle. Read online free On The Hypersonic Flow Past Blunted Flat Delta Wings ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author | : Arnold Polak |
Publisher | : |
Total Pages | : 48 |
Release | : 1970 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
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 | : |
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 | : Bernard Mazelsky |
Publisher | : |
Total Pages | : 86 |
Release | : 1968 |
Genre | : |
ISBN | : |
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 | : Bernard Mazelsky |
Publisher | : |
Total Pages | : 82 |
Release | : 1967 |
Genre | : |
ISBN | : |
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 | : Norman D. Malmuth |
Publisher | : |
Total Pages | : 66 |
Release | : 1965 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Author | : Joseph L. Francis |
Publisher | : |
Total Pages | : 82 |
Release | : 1966 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 86 |
Release | : 1967 |
Genre | : |
ISBN | : |
Author | : Shivakumar Srinivasan |
Publisher | : |
Total Pages | : |
Release | : 1991 |
Genre | : |
ISBN | : |
Author | : Alexander B. Lessin |
Publisher | : |
Total Pages | : |
Release | : 1993 |
Genre | : |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 56 |
Release | : 1966 |
Genre | : |
ISBN | : |