Interaction Of Moving Shocks And Hot Layers
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Interaction Of Moving Shocks And Hot Layers
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Author : Robert V. Hess
language : en
Publisher:
Release Date : 1957
Interaction Of Moving Shocks And Hot Layers written by Robert V. Hess and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Gas dynamics categories.
This paper treats the interaction between hot layers extended along the wall and normal or oblique shocks moving over them. Emphasis is on the cases of large hot-layer temperatures and strong shock waves for which small-perturbation theories are not applicable. A variety of possible interaction patterns are described. Of greatest interest are the more extreme cases when the hot layer is forced to accumulate in a growing bubble-like region bound to the moving shock, and some of the cold air above the layer moves around the bubble and interposes a high-speed forward-moving cold jet between the wall and the bubble. For some cases, especially with oblique shocks, this reverse jet may not form. Mixing will eventually limit the size of the bubble and make its characteristics more nearly like those of the more familiar separation bubbles. The effects of viscosity at the wall remains essentially different, however, since the shock is moving relative to the wall.
Technical Note National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1957
Technical Note National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aeronautics categories.
Shock Wave Boundary Layer Interactions
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Author : Holger Babinsky
language : en
Publisher: Cambridge University Press
Release Date : 2011-09-12
Shock Wave Boundary Layer Interactions written by Holger Babinsky and has been published by Cambridge University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011-09-12 with Technology & Engineering categories.
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.
Index Of Naca Technical Publications
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1954
Index Of Naca Technical Publications written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Aeronautics categories.
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6
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Author : C. Herbert Law
language : en
Publisher:
Release Date : 1975
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions At Mach 6 written by C. Herbert Law and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Aerodynamic heating categories.
Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.
Monthly Catalog Of United States Government Publications
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Author :
language : en
Publisher:
Release Date : 1957
Monthly Catalog Of United States Government Publications written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Government publications categories.
Annual Report Of The National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1951
Annual Report Of The National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aeronautics categories.
Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.
Effect Of Shock Impingement On The Distribution Of Heat Transfer Coefficients On A Right Circular Cylinder At Mach Numbers Of 2 65 3 51 And 4 44
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Author : Robert A. Newlander
language : en
Publisher:
Release Date : 1961
Effect Of Shock Impingement On The Distribution Of Heat Transfer Coefficients On A Right Circular Cylinder At Mach Numbers Of 2 65 3 51 And 4 44 written by Robert A. Newlander and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Fluid mechanics categories.
Boundary Layer Research
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Author : International Union of Theoretical and Applied Mechanics
language : en
Publisher:
Release Date : 1958
Boundary Layer Research written by International Union of Theoretical and Applied Mechanics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Aerodynamics categories.
Computation Of Viscous Shock Shock Hypersonic Interactions With An Implicit Flux Split Scheme
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Author : Datta V. Gaitonde
language : en
Publisher:
Release Date : 1990
Computation Of Viscous Shock Shock Hypersonic Interactions With An Implicit Flux Split Scheme written by Datta V. Gaitonde and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamics, Hypersonic categories.
The interaction of an impinging shock with the bow-shock generated by a blunt geometry is examined numerically for hypersonic (Mach 8, perfect gas) flows with modified Steger-Warming flux-split scheme. The modifications are designed to reduce numerical dissipation in the boundary layer thus improving the resolution and accuracy of the resulting algorithm. The full 2-D Navier- Stokes equations are solved in finite-volume formulation with central differencing for viscous terms and residual driven line Gauss-Seidel relaxation for time advancement. Grid resolution studies are performed. For a Type IV interaction, comparison with surface pressure and heat-transfer rates display good overall agreement with experimental values. For a Type III+ interaction, a detailed comparison is made with experimental surface quantities and a computation with Van Leer's flux-splitting algorithm. The peak amplification of pressure is modestly overpredicted with the current algorithm. The computed peak heat transfer is comparable to that obtained in previous research with Van Leer's splitting, although anomalous behavior is observed in the vicinity of the stagnation point. This behavior may be eliminated with appropriate corrections.