Download or read book Effects of Wall Cooling and Leading edge Blunting on Ramp induced Laminar Flow Separations at Mach Numbers from 3 Through 6 written by J. Don Gray and published by . This book was released on 1972 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of wall cooling and nose bluntness on laminar and transitional reattaching flows induced by a 9.5-degree ramp were investigated at Mach numbers from 3 through 6 measuring the longitudinal surface pressure and heat-transfer rate distributions, as well as the flow-field pressures, at several longitudinal stations. Reynolds number based on flat-plate length was varied from 0.25 to 1.0 million. The trend in the change in interaction length with Reynolds number increase indicated laminar reattachment at all test Reynolds numbers at M = 6 and transitional at the two higher Reynolds numbers at M = 3.

Download or read book Effects of Wall Cooling and Leading Edge Blunting on Ramp Induced Laminar Flow Separations at Mach Numbers from 3 Through 6 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of wall cooling and nose bluntness on laminar and transitional reattaching flows induced by a 9.5-degree ramp were investigated at Mach numbers from 3 through 6 measuring the longitudinal surface pressure and heat-transfer rate distributions, as well as the flow-field pressures, at several longitudinal stations. Reynolds number based on flat-plate length was varied from 0.25 to 1.0 million. The trend in the change in interaction length with Reynolds number increase indicated laminar reattachment at all test Reynolds numbers at M = 6 and transitional at the two higher Reynolds numbers at M = 3.

Download or read book Effects of Wall Cooling and Leading Edge Blunting on Ramp Induced Laminar Flow Separations at Mach Numbers from 3 Through 6 written by and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of wall cooling and nose bluntness on laminar and transitional reattaching flows induced by a 9.5-degree ramp were investigated at Mach numbers from 3 through 6 measuring the longitudinal surface pressure and heat-transfer rate distributions, as well as the flow-field pressures, at several longitudinal stations. Reynolds number based on flat-plate length was varied from 0.25 to 1.0 million. The trend in the change in interaction length with Reynolds number increase indicated laminar reattachment at all test Reynolds numbers at M = 6 and transitional at the two higher Reynolds numbers at M = 3.

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1972 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Collection of Technical Papers written by and published by . This book was released on 1972 with total page 1274 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements written by and published by . This book was released on 1972 with total page 1060 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1972 with total page 296 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 1974 with total page 592 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Index written by and published by . This book was released on 1972 with total page 916 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA SP written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering written by and published by . This book was released on 1992 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).

Download or read book Aeronautical Engineering A Cumulative Index to a Continuing Bibliography supplement 274 written by and published by . This book was released on 1992 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Shock Wave Boundary Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.

Download or read book Convective Heat Transfer in Planetary Gases written by Joseph G. Marvin and published by . This book was released on 1965 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Equilibrium convective heat transfer in several real gases was investigated. The gases considered were air, nitrogen, hydrogen, carbon dioxide, and argon. Solutions to the similar form of the boundary-layer equations were obtained for flight velocities to 30,000 ft/sec for a range of parameters sufficient to define the effects of pressure level, pressure gradient, boundary-layer-edge velocity, and wall temperature. Results are presented for stagnation-point heating and for the heating-rate distribution. For the range of parameters investigated the wall heat transfer depended on the transport properties near the wall and precise evaluation of properties in the high-energy portions of the boundary layer was not needed. A correlation of the solutions to the boundary-layer equations was obtained which depended only on the low temperature properties of the gases. This result can be used to evaluate the heat transfer in gases other than those considered. The largest stagnation-point heat transfer at a constant flight velocity was obtained for argon followed successively by carbon dioxide, air, nitrogen, and hydrogen. The blunt-body heating-rate distribution was found to depend mainly on the inviscid flow field. For each gas, correlation equations of boundary-layer thermodynamic and transport properties as a function of enthalpy are given for a wide range of pressures to a maximum enthalpy of 18,000 Btu/lb.

Download or read book American National Standard Inspection Procedures for School Buses written by and published by . This book was released on 1972 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Leading edge Bluntness and Ramp Deflection Angle on Laminar Boundary layer Separation in Hypersonic Flow written by James Courtland Townsend and published by . This book was released on 1966 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Numerical Solution of the Equations for Compressible Laminar Transitional and Turbulent Boundary Layers and Comparisons with Experimental Data written by Julius E. Harris and published by . This book was released on 1971 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical method for solving the equations for laminar, transitional, and turbulent compressible boundary layers for either planar or axisymmetric flows is presented. The fully developed turbulent region is treated by replacing the Reynolds stress terms with an eddy viscosity model. The mean properties of the transitional boundary layer are calculated by multiplying the eddy viscosity by an intermittency function based on the statistical production and growth of the turbulent spots. A specifiable turbulent Prandtl number relates the turbulent flux of heat to the eddy viscosity. A three-point implicit finite-difference scheme is used to solve the system of equations. The momentum and energy equations are solved simultaneously without iteration. Numerous test cases are compared with experimental data for supersonic and hypersonic flows; these cases include flows with both favorable and mildly unfavorable pressure gradient histories, mass flux at the wall, and traverse curvature.