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On The Hypersonic Flow Past Blunted Flat Delta Wings
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Book Synopsis On the Hypersonic Flow Past Blunted, Flat Delta Wings by : Arnold Polak
Download or read book On the Hypersonic Flow Past Blunted, Flat Delta Wings written by Arnold Polak and published by . This book was released on 1970 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis On the Hypersonic Flow Past Blunted, Flat Delta Wings by : Arnold Polak
Download or read book On the Hypersonic Flow Past Blunted, Flat Delta Wings written by Arnold Polak and published by . This book was released on 1970 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Research on Hypersonic Flow of Blunt Delta Wings. Part Ii. Gap Effects of a Blunt Slab Delta Wing at Moderate Supersonic and Hypersonic Speeds by : Bernard Mazelsky
Download or read book Research on Hypersonic Flow of Blunt Delta Wings. Part Ii. Gap Effects of a Blunt Slab Delta Wing at Moderate Supersonic and Hypersonic Speeds written by Bernard Mazelsky and published by . This book was released on 1968 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis 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 by : Bernard Mazelsky
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 Synopsis On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges by : Norman D. Malmuth
Download or read book On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges written by Norman D. Malmuth and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Hypersonic Flow Over Delta Wings at High Angles of Attack by : Joseph L. Francis
Download or read book Hypersonic Flow Over Delta Wings at High Angles of Attack written by Joseph L. Francis and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research on Hypersonic Flow of Blunt Delta Wings by :
Download or read book Research on Hypersonic Flow of Blunt Delta Wings written by and published by . This book was released on 1967 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Navier-Stokes Computations of Hypersonic Flow Past a Blunt Edge Delta Wing at Several Angles of Attack by : Shivakumar Srinivasan
Download or read book Navier-Stokes Computations of Hypersonic Flow Past a Blunt Edge Delta Wing at Several Angles of Attack written by Shivakumar Srinivasan and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Abnormal Peaks of Increased Heat-transfer on the Blunted Delta Wing in the Hypersonic Flow by : Alexander B. Lessin
Download or read book Abnormal Peaks of Increased Heat-transfer on the Blunted Delta Wing in the Hypersonic Flow written by Alexander B. Lessin and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research on Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack by :
Download or read book Research on Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack written by and published by . This book was released on 1966 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Viscous Flow Past a Flat Delta Wing at Moderate Angle of Attack by : Arnold Polak
Download or read book Hypersonic Viscous Flow Past a Flat Delta Wing at Moderate Angle of Attack written by Arnold Polak and published by . This book was released on 1966 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a study of the three-dimensional boundary layer over the windward side of a flat delta wing in hypersonic flow at a moderate angle of attack. The interaction between the inviscid and the viscous flow region is analyzed, and its effect is taken into account. The theory is developed for thin flat delta wings with the shock detached from the leading edges and attached at the apex. The inviscid solution based on the Newtonian-conical flow theory of Messiter-Hida has been matched to the three-dimensional boundary layer solution over the wing. The transverse velocity component normal to the conical ray is small and a perturbation method leads to a system of ordinary differential equations. The solution of these equations together with the tangent-cone method is used to study the viscous-inviscid interaction. The results are applied to calculate the streamline pattern, induced pressure, skin drag and heat transfer over the wing surface. The present theory is in general agreement with the available experimental data. (Author).
Book Synopsis Research on Hypersonic Flow of Blunt Delta Wings. Part Iii. Gap Effects of a Blunt Slab Delta Wing at Moderate Supersonic and Hypersonic Speeds by : Bernard Mazelsky
Download or read book Research on Hypersonic Flow of Blunt Delta Wings. Part Iii. Gap Effects of a Blunt Slab Delta Wing at Moderate Supersonic and Hypersonic Speeds written by Bernard Mazelsky and published by . This book was released on 1968 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Numerical Simulation of Hypersonic Flow Over a Blunt Delta Wing by : Kuok-Ming Lee
Download or read book Numerical Simulation of Hypersonic Flow Over a Blunt Delta Wing written by Kuok-Ming Lee and published by . This book was released on 1989 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing by : Kuok-Ming Lee
Download or read book Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing written by Kuok-Ming Lee and published by . This book was released on 1989 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer Measurements on a Delta Wing with Blunted Leading Edges in Hypersonic Flow by : Bo Lemcke
Download or read book Heat Transfer Measurements on a Delta Wing with Blunted Leading Edges in Hypersonic Flow written by Bo Lemcke and published by . This book was released on 1975 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flow Fields, Pressure Distributions, and Heat Transfer for Delta Wings at Hypersonic Speeds by : Mitchel H. Bertram
Download or read book Flow Fields, Pressure Distributions, and Heat Transfer for Delta Wings at Hypersonic Speeds written by Mitchel H. Bertram and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
