Download or read book Effect of Distributed Three dimensional Roughness and Surface Cooling on Boundary layer Transition and Lateral Spread of Turbulence at Supersonic Speeds written by Albert L. Braslow and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation by Schlieren Technique of Methods of Fixing Fully Turbulent Flow on Models at Supersonic Speeds written by Mary W. Jackson and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 984 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1961 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.
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.
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1959 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of NASA Technical Publications written by and published by . This book was released on 1959 with total page 494 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 1957 with total page 860 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of N A S A Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1958 with total page 498 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1966 with total page 424 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1961-10 with total page 1540 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Publications Announcements with Indexes written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 1556 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book WADC Technical Report written by United States. Wright Air Development Division and published by . This book was released on 1959 with total page 1318 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Transfer in Structures written by H. Schuh and published by Elsevier. This book was released on 2014-05-16 with total page 359 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat Transfer in Structures discusses the heat flow problems directly related to structures. A large section of the book presents the heat conduction in solids. The fundamentals of the analytical method are covered briefly, while introduction on the use of semi-analytical methods is treated in detail. Various approximate methods and finite difference methods are fully explained. The description of structural elements is dealt with extensively. The subject of analogues for finding temperature distributions are briefly discussed, while similarity laws and model testing are covered more comprehensively. Another topic of interest is the heat flow inside the solid part of an ablating body which is covered in detail. Thermal conductance across interfaces and joints are analyzed. And a thorough discussion of the steady heat flow is provided. A section of the text covers the simple structural elements. The book will provide useful information to aeronautics, astronautics, mechanics, engineers, and students of the physical sciences.
Download or read book Stability of Parallel Flows written by R. Betchov and published by Elsevier. This book was released on 2012-12-02 with total page 345 pages. Available in PDF, EPUB and Kindle. Book excerpt: Stability of Parallel Flows provides information pertinent to hydrodynamical stability. This book explores the stability problems that occur in various fields, including electronics, mechanics, oceanography, administration, economics, as well as naval and aeronautical engineering. Organized into two parts encompassing 10 chapters, this book starts with an overview of the general equations of a two-dimensional incompressible flow. This text then explores the stability of a laminar boundary layer and presents the equation of the inviscid approximation. Other chapters present the general equations governing an incompressible three-dimensional flow, which requires the massive use of a computer. This book discusses as well the experimental studies on the oscillations of the boundary layer wherein the mean flow is affected by the presence of oscillations. The final chapter describes the concept of the stability of turbulent flows found in boundary layers, wakes, and jets. This book is a valuable resource for physicists, mathematicians, engineers, scientists, and researchers.
Download or read book Symposia written by Defense Documentation Center (U.S.) and published by . This book was released on 1963 with total page 290 pages. Available in PDF, EPUB and Kindle. Book excerpt:
