Download or read book Calculation of Optimum Supersonic Delta Wings written by Julian H. Kainer and published by . This book was released on 1967 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the distributed and total drag-due-to-lift in closed form by means of linearized supersonic wing theory for delta wings having arbitrary warp described by a symmetrical ten-term power series expansion for which the loading was reported on previously by the author and others. For both sonic and supersonic leading edges one hundred drag contributions are derived, ninety of which are interference terms induced by the interaction of each loading with each of the noncorresponding downwashes. For subsonic leading edges additional terms are included to account for the suction forces induced by the leading edge pressure singularities. The mean chord shape required to deflect under aeroelastic load to the desired shape computed was programmed for the IBM 704 Digital Computer. (Author).
Download or read book Wing Theory in Supersonic Flow written by Elie Carafoli and published by Elsevier. This book was released on 2013-10-22 with total page 611 pages. Available in PDF, EPUB and Kindle. Book excerpt: Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Download or read book Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges written by Y. C. Vigneron and published by . This book was released on 1978 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Calculations by a First Order Theory of Supersonic Flow Around Delta Wings written by and published by . This book was released on 1980 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Trim Drag at Supersonic Speeds of Various Delta planform Configurations written by M. E. Graham and published by . This book was released on 1960 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Damping in Roll of Cruciform and Some Related Delta Wings at Supersonic Speeds written by Herbert S. Ribner and published by . This book was released on 1951 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping in roll of cruciform delta wings in supersonic flow has been evaluated by means of small-disturbance (linearized) wing theory; both subsonic and supersonic component stream velocities normal to the leading edges have been considered. In addition, some known two-dimensional results for rotating multibladed laminae have been applied to obtain the loading when the number of panels is changed from four to an arbitrary number, under the restriction of low aspect ratio; the damping in roll has been determined explicitly for three panels. Finally, the damping for an inifinite number of panels has been evaluated without restriction as to aspect ratio or Mach number.
Download or read book Computation of Supersonic Flow over Flying Configurations written by Adriana Nastase and published by Elsevier. This book was released on 2010-07-07 with total page 425 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computation of Supersonic Flow over Flying Configurations is a high-level aerospace reference book that will be useful for undergraduate and graduate students of engineering, applied mathematics and physics. The author provides solutions for three-dimensional compressible Navier-Stokes layer subsonic and supersonic flows. Computational work and experimental results show the real-world application of computational results Easy computation and visualization of inviscid and viscous aerodynamic characteristics of flying configurations Includes a fully optimized and integrated design for a proposed supersonic transport aircraft
Download or read book An Integrated Approach to the Analysis and Design of Wings and Wing body Combinations in Supersonic Flow written by Ralph L. Carmichael and published by . This book was released on 1966 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book On the Calculation of Unsteady Nonlinear Three dimensional Supersonic Flow Past Wings written by Stanford University. Department of Aeronautics and Astronautics and published by . This book was released on 1968 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author).
Download or read book Computer Program for Calculating Supersonic Flow on the Windward Side of Conical Delta Wings by the Method of Lines written by E. B. Klunker and published by . This book was released on 1972 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Proper Combination of Lift Loadings for Least Drag on a Supersonic Wing written by Frederick C. Grant and published by . This book was released on 1955 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The best combination of four loadings on a delta wing with subsonic leading edges is calculated for several Mach numbers as a numerical example. The loadings considered have finite pressures everywhere on the plan form. At each Mach number the optimum combination of the four non-singular loadings has about the same drag coefficient as a flat plate with leading-edge thrust.
Download or read book Investigation of Methods for Computing Flutter Characteristics of Supersonic Delta Wings and Comparison with Experimental Data written by Charles Harold Wilts and published by . This book was released on 1959 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reduction of Drag Due to Lift at Supersonic Speeds written by Douglas Aircraft Company and published by . This book was released on 1955 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: $EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Download or read book Effect of a Finite Trailing edge Thickness on the Drag of Rectangular and Delta Wings at Supersonic Speeds written by E. B. Klunker and published by . This book was released on 1952 with total page 690 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of a finite trailing-edge thickness on the pressure drag of rectangular and delta wings with truncated diamond-shaped airfoil sections with a given thickness ratio is studied for supersonic Mach numbers, linearized theory being used to evaluate the surface pressures. In order to facilitate comparison with wings having sharp trailing edges, the position of maximum thickness and base height are determined for least thickness and base height are determined for least pressure drag as functions of a base-pressure parameter. Comparison is then made between the drag of these wings and similar wings with a sharp trailing edge for various aspect ratios and thickness ratios as a function of stream Mach number. The calculations of the drag characteristics for these wings show that significant drag characteristics for these wings show that significant drag reductions are possible under some condtions at high supersonic speeds. These reductions are relatively independent of aspect ratio for the rectangular wings but depend considerably on aspec ratio for the delta wings; the smaller aspect ratios show the larger drag reductions. Calculations of the spanwise distribution of drag are included to compare further the effect of a base on the drag fro different aspect ratios.
Download or read book Numerical Methods for the Design and Analysis of Wings at Supersonic Speeds written by Harry W. Carlson and published by . This book was released on 1974 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measured and Predicted Section Wave Drag Coefficients at a Mach Number of 1 6 for a Delta Wing with Two Airfoil Sections written by Frederick C. Grant and published by . This book was released on 1959 with total page 56 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 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.
