Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Download An Exact Theory Of Supersonic Flow Around A Delta Wing full books in PDF, epub, and Kindle. Read online An Exact Theory Of Supersonic Flow Around A Delta Wing ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author : L. R. Fowell
Publisher :
ISBN 13 :
Total Pages : 92 pages
Book Rating : 4.:/5 (713 download)
Download or read book An Exact Theory of Supersonic Flow Around a Delta Wing written by L. R. Fowell and published by . This book was released on 1955 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (945 download)
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:
Author : Elie Carafoli
Publisher : Elsevier
ISBN 13 : 1483160270
Total Pages : 611 pages
Book Rating : 4.4/5 (831 download)
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.
Author : Herbert S. Ribner
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.3/5 (91 download)
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.
Author : Joseph Henry Clarke
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.E/5 ( download)
Download or read book Uniform Second-order Solution for Supersonic Flow Over Delta Wing Using Reverse-flow Integral Method written by Joseph Henry Clarke and published by . This book was released on 1963 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of supersonic flow over an inclined flatplate delta wing with supersonic edges is solved to second order in incidence. This solution for surface pressure is uniform and fully analytic. The approach utilizes a reverse-flow integral method previously developed for secondorder problems. This method is augmented by a number of techniques appropriate to its framework. The simplification over standard techniques acgieved by using these reverse-flow methods is quite substantial and makes the problem tractible. Reverse-flow procedures give a volume-surface integral relation that connects the second-order forward flow over the body of interest with the linearized reverse-flow over a related body. A singular integral equation is generated from the integral relation by introducing the edge sweep of the reverse-flow wing as a free parameter. An inversion is available which gives the second-order solution on the surface of the wing. The solution is then made uniformly valid using techniques previously developed. (Author).
Author : Ralph L. Carmichael
Publisher :
ISBN 13 :
Total Pages : 18 pages
Book Rating : 4.:/5 (31 download)
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:
Author : R.C.F. Bartels
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.3/5 (91 download)
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:
Author : Y. C. Vigneron
Publisher :
ISBN 13 :
Total Pages : 86 pages
Book Rating : 4.:/5 (317 download)
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 Supersonic Flow Over Low Aspect-ratio Wings written by and published by . This book was released on 1911 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: An attempt has been made, by means of exp": rimental work, to consolidate and augment existing knowledge of high-speed flows over delta wings. Particular emphasis . is placed on the investigation of flows which did not confirm to the 'accepted' pattern. In Part 1 the flow regimes on a caret wing are discussed with particular emphasis placed on the occurrence of 'strong' oblique shocks. Results are presented which demonstrate that when viewed in direction normal to the leading edge, shocks of both the 'weak' and the 'strong' families can be said to exist. An experiment designed to produce a single strong shock by means of a caret wingýof large anhedral, instead gave rise to a complex multiple shock pattern which could not be adequately explained by exact inviscid theory. In Part 2 the unexpected pressure rises reported on the lee surfaces of various delta wings (References 22 and 23) are shown to be, at least in part, the result of interference from the model support and base-mounted instrumentation. The physical reason for the pressure rise is discussed. 'Correct' leeside pressure distributions are pre- sented for one of the models used in Reference 23 for angles of attack up to 50 degrees. In Part 3 the different flow regimes on delta wings are discussed together with the methods of defining the boundaries between them. The conjecture that thin shock-layer theory can be used to predict the on- set of leading-edge separation is carefully investigated by means of tunnel tests on a particular wing with triangular cross-section.
Author : Norman D. Malmuth
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.:/5 (318 download)
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.
Author : Adriana Nastase
Publisher : Elsevier
ISBN 13 : 008055699X
Total Pages : 425 pages
Book Rating : 4.0/5 (85 download)
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
Author : Stanford University. Department of Aeronautics and Astronautics
Publisher :
ISBN 13 :
Total Pages : 106 pages
Book Rating : 4.F/5 ( download)
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).
Author : Eugene A. Carpovich
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (31 download)
Download or read book The Drag of a Delta Wing in Supersonic Flow written by Eugene A. Carpovich and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John Wilder Miles
Publisher :
ISBN 13 :
Total Pages : 244 pages
Book Rating : 4.3/5 (243 download)
Download or read book The Potential Theory of Unsteady Supersonic Flow written by John Wilder Miles and published by . This book was released on 1980 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 54 pages
Book Rating : 4.:/5 (317 download)
Download or read book Leeward Flow Over Delta Wings at Supersonic Speeds written by and published by . This book was released on 1980 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : A. Robinson
Publisher : Cambridge University Press
ISBN 13 : 1107622654
Total Pages : 583 pages
Book Rating : 4.1/5 (76 download)
Download or read book Wing Theory written by A. Robinson and published by Cambridge University Press. This book was released on 2013-09-12 with total page 583 pages. Available in PDF, EPUB and Kindle. Book excerpt: First published in 1956 as part of the Cambridge Aeronautical Series, this book addresses the vital science of wing theory. Robinson and Laurmann record the historic developments in wing theory, including the work of Joukowski and Bernoulli, and discuss developments in supersonic flow and unsteady aerofoil theory. This book will be of value to anyone with an interest in the history of the science of flight.
Author : Arthur ROBINSON (M.Sc., A.F.R.Ae.S., and TOD (Sir John Hunter Hunter) K.B.E.)
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (54 download)
Download or read book Bound and Trailing Vortices in the Linearised Theory of Supersonic Flow, and the Downwash in the Wake of a Delta Wing written by Arthur ROBINSON (M.Sc., A.F.R.Ae.S., and TOD (Sir John Hunter Hunter) K.B.E.) and published by . This book was released on 1952 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
