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Author : D. I. A. Poll
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book The Effect of Wing Sweep Back Upon Transition in Hypersonic Flow written by D. I. A. Poll and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Gary T. Chapman
Publisher :
ISBN 13 :
Total Pages : 1 pages
Book Rating : 4.:/5 (227 download)
Download or read book Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds written by Gary T. Chapman and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of crossflow and shock strength on transition of the laminar boundary layer behind a swept leading edge have been investigated analytically and with the aid of available experimental data. An approximate method of determining the crossflow Reynolds number on a leading edge of circular cross section at supersonic speeds is presented. The applicability of the critical crossflow criterion described by Owen and Randall for transition on swept wings in subsonic flow was examined for the case of supersonic flow over swept circular cylinders. A wide range of applicability of the subsonic critical values is indicated. The corresponding magnitude of crossflow velocity necessary to cause instability on the surface of a swept wing at supersonic speeds was also calculated and found to be small. The effects of shock strength on transition caused by Tollmien-Schlichting type of instability are discussed briefly. Changes in local Reynolds number, due to shock strength, were found analytically to have considerably more effect on transition caused by Tollmien-Schlichting instability than on transition caused by crossflow instability. Changes in the mechanism controlling transition from Tollmien-Schlichting instability to crossflow instability were found to be possible as a wing is swept back and to result in large reductions in the length of laminar flow. (Author).
Author : Kenneth F. Stetson
Publisher :
ISBN 13 :
Total Pages : 116 pages
Book Rating : 4.3/5 (91 download)
Download or read book Comments on Hypersonic Boundary-layer Transition written by Kenneth F. Stetson and published by . This book was released on 1990 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
Author : Max A. Heaslet
Publisher :
ISBN 13 :
Total Pages : 726 pages
Book Rating : 4.F/5 ( download)
Download or read book The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms written by Max A. Heaslet and published by . This book was released on 1948 with total page 726 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.
Author : Norman D. Malmuth
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.E/5 ( 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 60 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 : Roger L. Kimmel
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.3/5 (91 download)
Download or read book The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers written by Roger L. Kimmel and published by . This book was released on 1993 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7 degrees half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.
Author : G. G. Chernyi
Publisher : Academic Press
ISBN 13 : 1483271684
Total Pages : 277 pages
Book Rating : 4.4/5 (832 download)
Download or read book Introduction to Hypersonic Flow written by G. G. Chernyi and published by Academic Press. This book was released on 2013-10-22 with total page 277 pages. Available in PDF, EPUB and Kindle. Book excerpt: Introduction to Hypersonic Flow has been made available to the English speaking reader because of its usefulness for those individuals desirous of obtaining an introduction to the subject. Written by an internationally acknowledged expert in the field of hypersonic flow, the book makes available heretofore unpublished Soviet work, as well as published work little known outside the Soviet Union. The author has however made every effort to include, where appropriate. Western references for the work he discusses. Starting with a general introductory chapter on hypersonic aerodynamics and aerodynamic problems, the remainder of the book concentrates on the inviscid, perfect fluid aspects of hypersonic flow, with emphasis on the fundamental concepts and rational methods of calculation. The book is directed to students of aerodynamics and gas dynamics, as well as to scientists and engineers interested in problems of hypersonic flight. The level of approach is such that it should prove particularly useful as an undergraduate and introductory graduate text.
Author :
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Transition Fixing for Hypersonic Flow written by and published by . This book was released on 1967 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : W. D. Vann
Publisher :
ISBN 13 :
Total Pages : 91 pages
Book Rating : 4.:/5 (175 download)
Download or read book Hypersonic Flow Over Blunt Slab Wings with Sweep Angles from 0 to 70 Degrees written by W. D. Vann and published by . This book was released on 1964 with total page 91 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental and theoretical investigation was made to determine the pressure distributions over swept wings in hypersonic flow. Two models having hemicylindrical leading edges were tested in the Aerospace Research Laboratories' 20-inch hypersonic wind tunnel. Tests were made over an angle-of-attack range of =25 degrees at five-degree increments for the sweep angles 0, 50, 60, and 70 degrees at a nominal test Mach number of 14 and a Reynolds number of 35,000 based on the nose diameter of the models. The test data measured on the nose region was in fair agreement with the theoretical pressure distributions for each sweep angle and appeared to be independent of Mach number as expected. At angles of attack up to 15 and 25 degrees, the flow over the expansion and compression surfaces appeared to be two-dimensional. Fairly good agreement was obtained between the measured test data and an inviscid theoretical analysis based on a modification of the blast wave theory. (Author).
Author :
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (317 download)
Download or read book Hypersonic Aerodynamic Characteristics of a Reentry Configuration with Variable-sweep Wings written by and published by . This book was released on 1964 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : H. L. Boerrigter
Publisher :
ISBN 13 :
Total Pages : 17 pages
Book Rating : 4.:/5 (11 download)
Download or read book On the Effect of Flowfield Non-uniformities on Boundary Layer Transition in Hypersonic Flow written by H. L. Boerrigter and published by . This book was released on 1995 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Joseph L. Francis
Publisher :
ISBN 13 :
Total Pages : 82 pages
Book Rating : 4.E/5 ( download)
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:
Author : S. Shahpar
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Transition Correlations for Hypersonic Flows Over Swept Surfaces written by S. Shahpar and published by . This book was released on 1997 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Marcus O. Creager
Publisher :
ISBN 13 :
Total Pages : 45 pages
Book Rating : 4.:/5 (137 download)
Download or read book Effect of Leading-edge Sweep and Surface Inclination on the Hypersonic Flow Field Over a Blunt Flat Plate written by Marcus O. Creager and published by . This book was released on 1959 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Oliver Taylor
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (111 download)
Download or read book Effects of Surface Roughness on Boundary Layer Transition in a Hypersonic Flow written by Oliver Taylor and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Allen Hallett Whitehead
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.:/5 (269 download)
Download or read book A Study of Pressure and Heat Transfer Over an 80° Sweep Slab Delta Wing in Hypersonic Flow written by Allen Hallett Whitehead and published by . This book was released on 1965 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Roger Dunlap
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (495 download)
Download or read book Effects of Cooling on Transition in the Boundary Layer on a Hemisphere in Simulated Hypersonic Flow written by Roger Dunlap and published by . This book was released on 1961 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study was made to investigate the effects of cooling on transition in the boundary layer on the nose of a 9-inch diameter hemisphere in simulated hypersonic flow, with the aim of gaining some knowledge of the circumstances under which boundary-layer cooling may promote a reduction in transition Reynolds number (transition reversal). The influences of cooling in increasing the stability to Tollmien-Schlichting type disturbances, in decreasing any stabilizing effects of convex curvature, and in increasing the magnitude of disturbances from fixed roughness elements, are discussed.
