Download or read book Analytical Investigation of the Effects of a Diffusion Field on a Laminar Boundary Layer in Supersonic Flow written by John Russell Radbill and published by . This book was released on 1958 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Effects of a Diffusion Field on a Laminar Boundary Layer in Supersonic Flow written by S. William Gouse and published by . This book was released on 1957 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book AFOSR written by United States. Air Force. Office of Scientific Research and published by . This book was released on 1957 with total page 1136 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book U S Government Research Reports written by and published by . This book was released on 1964 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Boundary Layer Transition at Supersonic Speeds written by E. R. Van Driest and published by . This book was released on 1961 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.

Download or read book U S Government Research Development Reports written by and published by . This book was released on 1968 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comprehensive Dissertation Index written by and published by . This book was released on 1984 with total page 914 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book International Aerospace Abstracts written by and published by . This book was released on 1995 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1952 with total page 498 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1993 with total page 354 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 Keywords Index to U S Government Technical Reports written by and published by . This book was released on 1962-12 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Keywords Index to U S Government Technical Reports permuted Title Index written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1962 with total page 860 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of the Effect of Surface Heating on Boundary layer Transition on a Flat Plate in Supersonic Flow written by Robert W. Higgins and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition has been studied on a heated flat plate in an air stream at a Mach number of 2.40 and a length Reynolds number range from 475,000 to 3,930,000. The transition region was investigated at nominal plate temperature levels of 60, 100, 140, 180, and 260 degrees F and depicted in a series of curves of transition Reynolds numbers, based on boundary-layer dimensions and fluid properties evaluated alternatively at free-stream and wall temperatures. The average skin-friction coefficient over the laminar portion of the boundary layer was determined.

Download or read book Publications from the Institute written by Massachusetts Institute of Technology and published by . This book was released on 1957 with total page 1164 pages. Available in PDF, EPUB and Kindle. Book excerpt: