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:
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).
Download or read book Hypersonic Longitudinal Trim Stability and Control Characteristics of a Delta wing Configuration at High Angles of Attack written by William H. Close and published by . This book was released on 1960 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Flow of Blunt Delta Wings at Low Angles of Attack I Shock Wave Shape and Surface Pressure Distribution written by Bernard Mazelsky and published by . This book was released on 1966 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
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.
Download or read book An Analysis of the Delta wing Hypersonic Stability and Control Behavior at Angles of Attack Between 30 and 90 written by David E. Fetterman and published by . This book was released on 1963 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
Download or read book The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50 written by John B. McDevitt and published by . This book was released on 1960 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book An Experimental Study of the Pressure and Heat transfer Distribution on a 70 Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Unsteady Aerodynamics of Delta Wings Performing Maneuvers to High Angle of Attack written by Mohammad-Ameen M. Jarrah and published by . This book was released on 1988 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Aerodynamic Characteristics of Two Delta wing X 15 Airplane Configurations written by Theodore J. Goldberg and published by . This book was released on 1969 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic aerodynamic characteristics of delta wing x- 15 airplane configurations.
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).
Download or read book Supersonic Flow Past a Delta Wing at Angles of Attack and Yaw written by R.C.F. Bartels and published by . This book was released on 1948 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Velocity Field Over Delta Wings at High Angles of Attack written by Devin O. O'Dowd and published by . This book was released on 1999-02-01 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: The study of vortex breakdown over delta wings at high angles of attack (AOA) has been an interest to researchers, mathematicians, and aircraft designers for decades. It is a very hot topic as it relates to many aircraft being designed today and because no complete understanding exists. Most of the understanding that does exist comes in the form of the problems associated with vortex breakdown. Many question if it is possible to control the breakdown to avoid the problems and to aid the aircraft in maneuverability. The purpose of this study is to lay the foundation for future research at the University of Washington, so that the identity to the cause of the vortex breakdown may be found.
Download or read book Lee side Flow Over Delta Wings at Supersonic Speeds written by David S. Miller and published by . This book was released on 1985 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
