Download or read book The Expansion of a Supersonic Laminar Boundary Layer Around a Convex Corner written by James W. Gress and published by . This book was released on 1968 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Analysis of the Interaction of a Boundary Layer and the Corner expansion Wave in Supersonic Flow written by P. H. Oosthuizen and published by . This book was released on 1967 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical study of the effects of the wall boundary layer on the supersonic flow around a sharp convex corner is presented. Fundamentally different methods of analysis are adopted for laminar and for turbulent boundary layers. In the case of interactions involving laminar boundary layers, an analysis based on the use of classical boundary layer theory is used. Results of numerical calculations carried out using this analysis to predict the effects of the major governing parameters are presented. In all cases, a considerable upstream and downstream influence is predicted. A simplified form of this analysis, closely related to that of Curle, is also presented, this analysis leading to a simple set of explicit equations describing the flow quantities in the interaction region. Comparison of the simplified analysis with results obtained from the full analysis indicated, as is to be expected, that the simplified analysis will only give acceptable results for small expansion angles and moderate Mach numbers. In the case of turbulent boundary layer interactions, an analysis based on the assumption that there is no upstream influence and that the major portion of the expansion occurs in an effectively inviscid manner is adopted, the flow properties being calculated by the method of rotational characteristics. (Author).
Download or read book An Experimental Investigation of Boundary Layer Expansion Around a Convex Corner in Supersonic Flow written by Thomas Johani and published by . This book was released on 1968 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flow Downstream of an Expansion Corner in Supersonic Flow Considering Effects of Initial Boundary Layer written by Merritt Albert Thomas and published by . This book was released on 1968 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Estimate of Compressible Boundary Layer Development Around a Convex Corner in Supersonic Flow written by Brian Lindsay Hunt and published by . This book was released on 1964 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis of the effect of a sharp convex corner on the momentum thickness of a compressible, supersonic boundary layer flow is presented. The problem is attacked by a momentum integral technique in which an approximate pressure field is used. The shape factor is approximated by a simple expression which is also of general application. The main result of the analysis is an analytic expression for the ratio of the momentum thicknesses downstream and upstream of the corner. The results are also presented graphically over appropriate ranges of the major flow parameters. (Author).
Download or read book Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack written by Franklin K. Moore and published by . This book was released on 1951 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1982 with total page 1282 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book UTIAS Technical Note written by University of Toronto. Institute of Aerospace Studies and published by . This book was released on 1968 with total page 444 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Turbulent Boundary Layer on a Yawed Cone in a Supersonic Stream written by Willis H. Braun and published by . This book was released on 1959 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Investigation of Supersonic Laminar Separation in a Concave Corner written by Tsai An Lu and published by . This book was released on 1970 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: Separation and reattachment of a supersonic laminar boundary layer in a concave corner, due to a free interaction process, are investigated by the method of integral relations. The proposed total enthalpy profile, which is represented as a polynomial in the streamwise velocity component, can satisfy all the physical conditions in the attached and separated regions. As a result, the effect of wall cooling together with suction can be studied within a single framework. The solution runs smoothly through the separation and reattachment points without any difficulties. The numerical results contain all the known physical characteristics associated with laminar separation. A critical point is found downstream of the reattachment point. This provides a criterion for determining the initial point of the interaction region. A new computational procedure is suggested after careful consideration of the nature of this critical point. The integral curve which leads away from the critical point will be matched with the curve originating at the initial interaction point ahead of the corner. In this way smooth continuation of the boundary layer displacement thickness is made possible. The present method appears to be simpler, more direct, and more versatile than many existing integral methods. Its extension to apply to a wider class of problems is under consideration. (Author).
Download or read book UTIAS Technical Note written by and published by . This book was released on 1967 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Expansion Wave Boundary Layer Interaction in Supersonic Airflow Around Corners of Different Angles of Expansion and Varying Radii of Curvature written by Robin A. Chaplin and published by . This book was released on 1968* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Response of a Laminar Boundary Layer in Supersonic Flow to Small Amplitude Progressive Waves written by Peter W. Duck and published by . This book was released on 1989 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Laminar Boundary Layer Separation Near a Compression Corner written by Abdallah Antoun Sfeir and published by . This book was released on 1969 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed measurements were performed in the region of interaction of a laminar boundary layer with a compression corner at Mach numbers near 2.5. Different models were tested permitting variation in the angle of compression and the conditions downstream of reattachment. The heat flux and the resistance of equilibrium of a hot wire anemometer at any location in the flow field were measured. These measurements were supplemented by either the wall or the pitot pressure to compute all thermodynamic and dynamic variables. The results permitted verification of the hypothesis of zero normal pressure gradients when the compression angle is small and the boundary layer is laminar. The enthalpy in the separated bubble was constant and equal to the wall enthalpy of a flat plate with attached laminar boundary layer at the same Mach number. Evidence of a reversed flow with velocities approximately 5% of the free stream velocity was observed. The recompression along the separating streamline was found to be very nearly isentropic. Critical points were located in the reattachment region and a physical explanation proposed with special emphasis on the location of transition. (Author).
Download or read book The Hypersonic Laminar Boundary Layer Near a Sharp Expansion Corner written by Keith Jordis Victoria and published by . This book was released on 1969 with total page 254 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ACCELERATION OF A HYPERSONIC BOUNDARY LAYER APPROACHING A CORNER written by GeorgeR. Olsson, Arthur F. Messiter and published by . This book was released on 1968 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Laminar Boundary Layer on a Cone in Supersonic Flow with Uniform Mass Transfer written by Paul A. Libby and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A solution for the laminar boundary layer on a cone with uniform mass transfer is obtained. The velocity field is found for either suction or injection but the related solution for the energy field is subject to an energy balance at the exposed surface and is therefore valid only for injection. This latter solution is equally applicable to certain species fields as well. The present results along with those presented previously for the two-dimensional case permit a comparison of the effect of injection on boundary layers over two-dimensional and conical surfaces.
