Boundary Layer Transition in the Leading Edge Region of a Swept Cylinder in High Speed Flow
Author : Colin Phillip Coleman
Publisher :
Page : 212 pages
File Size : 22,44 MB
Release : 1998
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Author : Colin Phillip Coleman
Publisher :
Page : 212 pages
File Size : 22,44 MB
Release : 1998
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Author : Michael E. Tauber
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Page : 44 pages
File Size : 44,21 MB
Release : 1989
Category : Aerodynamic heating
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Author : H.F. Fasel
Publisher : Springer Science & Business Media
Page : 703 pages
File Size : 14,87 MB
Release : 2013-03-09
Category : Science
ISBN : 3662039974
The origins of turbulent flow and the transition from laminar to turbulent flow are among the most important unsolved problems of fluid mechanics and aerodynamics. Besides being a fundamental question of fluid mechanics, there are any number of applications for information regarding transition location and the details of the subsequent turbulent flow. The JUT AM Symposium on Laminar-Turbulent Transition, co-hosted by Arizona State University and the University of Arizona, was held in Sedona, Arizona. Although four previous JUT AM Symposia bear the same appellation (Stuttgart 1979, Novosibirsk 1984, Toulouse 1989, and Sendai 1994) the topics that were emphasized at each were different and reflect the evolving nature of our understanding of the transition process. The major contributions of Stuttgart 1979 centered on nonlinear behavior and later stages of transition in two-dimensional boundary layers. Stability of closed systems was also included with Taylor vortices in different geometries. The topics of Novosibirsk 1984 shifted to resonant wave interactions and secondary instabilities in boundary layers. Pipe- and channel-flow transition were discussed as model problems for the boundary layer. Investigations of free shear layers were presented and a heavy dose of supersonic papers appeared for the first time. The character of Toulouse 1989 was also different in that 3-D boundary layers, numerical simulations, streamwise vortices, and foundation papers on receptivity were presented. Sendai 1994 saw a number of papers on swept wings and 3-D boundary layers. Numerical simulations attacked a broader range of problems.
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Page : 836 pages
File Size : 11,93 MB
Release : 1994
Category : Aeronautics
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Author :
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Page : 772 pages
File Size : 34,38 MB
Release : 1970
Category : Mechanics, Applied
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Author : United States. Superintendent of Documents
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Page : 2106 pages
File Size : 32,8 MB
Release : 1959
Category : Government publications
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February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
Author : Nihon Kōkū Uchū Gakkai
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Page : 476 pages
File Size : 29,49 MB
Release : 1996
Category : Aerodynamics
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Author :
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Page : 538 pages
File Size : 17,96 MB
Release : 1991
Category : Aeronautics
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Author : Joseph G. Marvin
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Page : 60 pages
File Size : 44,42 MB
Release : 1965
Category : Heat
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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.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 716 pages
File Size : 45,14 MB
Release : 1956
Category : Aeronautics
ISBN :