2 edition of **hypersonic viscous shock layer with mass transfer** found in the catalog.

hypersonic viscous shock layer with mass transfer

S. Y. Chen

- 206 Want to read
- 32 Currently reading

Published
**1966** by Rand Corporation in Santa Monica, Calif .

Written in English

- Ablation (Aerothermodynamics),
- Aerodynamics, Hypersonic.

**Edition Notes**

Bibliography: p. 35.

Statement | S.Y. Chen, J. Aroesty, and R. Mobley. |

Series | Memorandum -- RM-4631-PR, Research memorandum (Rand Corporation) -- RM-4631-PR.. |

Contributions | Aroesty, Jerome., Mobley, R. L. |

The Physical Object | |
---|---|

Pagination | x, 35 p. : |

Number of Pages | 35 |

ID Numbers | |

Open Library | OL17984599M |

shock–shockinteractions generate additional compres-sion and expansion waves, and free shear layers. Simulating all the ﬂow features and the underlying ﬂow physics makes it harder to predict hypersonic shock/boundary-layer interactions than their supersonic counterparts. In this paper, we study hypersonic shock/boundary-layer. "The Effect of Wall Temperature on the Low Reynolds Number Hypersonic Stagnation Region Shock Layer" (J.T.C. Liu). International Journal of Heat and Mass Trans (). "Flow Induced by the Impulsive Motion of an Infinite Flat Plate in a Dusty Gas" (J.T.C. Liu). Astronautica A ().

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The present treatment of mass transfer into the hypersonic viscous shock layer is restricted to the injection of air into air and neglects all chemical effects by assuming that the equation of state is that of a single-component ideal gas. Certain higher-order effects, such as slip and temperature jump, are by: 7.

An investigation of the effects of surface mass transfer on the viscous hypersonic shock layer of a blunt body. Cheng's theory of the Newtonian shock layer is modified to include both suction and injection, and extensive numerical results are obtained for the injection of air into by: 7.

An investigation of the effects of surface mass transfer on the viscous hypersonic shock layer of a blunt body has been performed.

Cheng's theory of t Cited by: 7. Viscous Hypersonic Flow: Theory of Reacting and Hypersonic Boundary Layers (Dover Books on Engineering) [Dorrance, William H.] on *FREE* shipping on qualifying offers. Viscous Hypersonic Flow: Theory of Reacting and Hypersonic Boundary Layers (Dover Books on Engineering)4/5(2).

Hypersonic viscous shock-layer flow over a highly cooled sphere. Viscous flows over slender spherically blunted cones at large anglesof attack including mass-transfer and low Reynolds number effects. Hypersonic chemically reacting viscous shock layers over sphere-cones and by: Numerical hypersonic viscous shock layer with mass transfer book of three‐dimensional viscous shock layer using axisymmetric analog along the streamlines International Journal of Numerical Methods for Heat & Fluid Flow, Vol.

18, No. 1 An Engineering Method for Aerodynamic Heating Prediction of Biconic Configurations in 3-D Hypersonic FlowCited by: In book: 29th International Symposium on Shock Waves, Chapter: Nonequilibrium and Rarefaction Effects in Hypersonic Multicomponent Viscous Shock Layers, Publisher: Springer, Editors: Riccardo Author: Vladimir Riabov.

Hypersonic viscous shock layer in a swirling gas flow on a permeable surface The influence of the swirling of the flow on the nature of the asymptotic behavior of the viscous shock layer equations at large Reynolds numbers is studied. “Computation of hypersonic laminar viscous flow over body with mass transfer and for spin at angle-of Cited by: 3.

Simulation of hypersonic flows of viscous gases over blunt bodies is examined by solution of the equations of a viscous shock layer and the complete Navier-Stokes equations, together with Author: Vladimir Riabov.

of full viscous shock-layer (FVSL) and high-order viscous shock-layer (HVSL) (see Refs. It has been shown that both a body and a shock slip model are required with the VSL calculations to receive physically meaningful results at higher altitudes (in the range of 90 to km).

A detailed comparison of the resultsCited by: 1. Original iterative/marching method to solve viscous shock layer equations is presented.

The method is based on splitting of marching component of the pressure gradient onto hyperbolic part and a part that minimizes the elliptic part to a maximum degree that are then subjected to the global iterations procedure. The effects of surface combustion, gas-layer combustion, surface mass transfer, dissociation, and variation of gas properties with temperature and composition upon the characteristics of both laminar and turbulent boundary layers will all be treated in later chapters of this : Dover Publications.

The analysis, a three-dimensional hypersonic viscous shock layer approach in conjunction with a numerical solution procedure, is shown to be both applicable and accurate based on comparisons of heat-transfer distributions, surface pressure distributions, and leeward meridian flow-field profile measurements taken in a hypersonic wind by: 4.

Summary. In hypersonic flows the boundary layer thickness can be not small compared to the shock layer thickness, disturbances originated inside of the boundary layer, therefore, can not attenuate over the inviscid part of the shock layer so much that their reflection from the leading-edge shock wave can be left out of by: 8.

Viscous hypersonic flow: theory of reacting and hypersonic boundary layers | Dorrance, William H | download | B–OK. Download books for free. Find books. mass transfer layer equations potential interaction rate thus diffusion function reacting properties The linear stability of hypersonic, chemically reacting viscous shock layer on a sharp cone is studied subject to different approximations of the flow geometry and physics.

The basic state laminar flows investigated are usually obtained using a Parabolized Navier-Stokes (PNS) code specifically developed for this purpose.

MASS TRANSFER IN THE HYPERSONIC LOW REYNOLDS NUMBER VISCOUS LAYER* By Leon Goldberg and Sinclaire M, Scala "'Presented at the IAS 30th Annual Meeting New York City, New York, Janu Preprint No. R62SD07 Janu Research performed under the auspices of the United StatesFile Size: 2MB. numerical solution of the hypersonic viscous-shock-layer equations for laminar, transitional, and turbulent flows of a perfect gas over blunt axially symmetric bodies e.

anderson and james n. moss langley research center hampton, va. mar 1 rp''iifir»i Cited by: Home > Begell Digital Portal > Books > Hypersonic Aerodynamics and Heat Transfer. ISBN: ISBN Online Original iterative/marching method to solve viscous shock layer equations is presented.

vehicle heat transfer and thermal strength of constructions of variable mass and shape is developed for all stages of the modern. A modern treatment of hypersonic aerothermodynamics for students, engineers, scientists, and program managers involved in the study and application of hypersonic flight.

It assumes an understanding of the basic principles of fluid mechanics, thermodynamics, compressible flow, and heat transfer.

Ten chapters address: general characterization of hypersonic flows; basic 3/5(1). Preface1. An Introduction to Hypersonic Heat-transfer Problems The Boundary-layer Equations Surface-material-Boundary-layer Interactions4, The Dissociated Laminar Boundary Layer5.

Mass Transfer and Chemical Reactions in the Laminar Boundary Layer Leading-edge Bluntness, Shock-wave Interaction, and Vorticity Effects7.

Solutions are obtained for hypersonic viscous interaction along a flat plate in the presence of strong boundary-layer blowing, with inverse-square-root injection velocity, for laminar flow over a cold wall and with a power-law viscosity–temperature by: 2.

Shock Tube Application to the Study of Compressible Turbulent Boundary Layer with Mass Injection. Pages Parabolic Viscous Shock Layer Theory for 3D Hypersonic Gas Flow. Shock Waves @ Marseille I Book Subtitle Hypersonics, Shock Tube & Shock.

You can write a book review and share your experiences. Other readers will always be interested in your opinion of the books you've read. Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.

The articles in this book, translated from Russian, were contributed by the world's leading authorities on supersonic and hypersonic flows and heat transfer. This superb book addresses the physics and engineering aspects of ultra high-speed aerodynamic problems. Thorough coverage is given to an array of specific problem-solving equations.

Applications of Heat, Mass and Fluid Boundary Layers brings together the latest research on boundary layers where there has been remarkable advancements in recent years.

This book highlights relevant concepts and solutions to energy issues and environmental sustainability by combining fundamental theory on boundary layers with real-world industrial applications from. INVISCID HYPERSONIC FLOW OVER A BLUNT BODY WITH HIGH RATES OF MASS AND HEAT =SFEX3 By E. Dale Martin Ames Research Center SUMMARY A study of steady hypersonic flow over a blunt body with a very high rate of continuous mass transfer fromthe body Surface, with heat conduction, is Size: 1MB.

This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is 4/5(1).

As a body's Mach number increases, the density behind a bow shock generated by the body also increases, which corresponds to a decrease in volume behind the shock due to conservation of mass.

Consequently, the distance between the bow shock and the body decreases at higher Mach numbers. Entropy layer. The first case was a steady two‐dimensional shock/boundary layer interaction on a flat plate with a mixture of N2 and O2 in the freestream. It was found that the real gas effects reduce the size of the shock induced separation bubble and the magnitude of the surface heating by: Michael Shi-Yuan Chen.

The Viscous Hypersonic Slender-Body Problem: A Numerical Approach Based on a System of Composite Equations Magnetic Hypersonic Flow Near the Stagnation Point at Low Reynolds Number The Hypersonic Viscous Shock Layer with Mass Transfer We then perform the numerical simulation of hypersonic viscous flow over a cylinder at Mach 8 and at different Knudsen numbers.

We carry out the study using the modified SLAU2 and the classical Roe schemes. We study how the shock anomalies found in the continuum hypersonic flows behave with the degree of : Ashwani Assam, M.

Nived, Nikhil Narayan Kalkote, Vinayak Eswaran. This superb book addresses the physics and engineering aspects of ultra high-speed aerodynamic problems. Thorough coverage is given to an array of specific problem-solving equations. Super- and Hypersonic Aerodynamics and Heat Transfer will be essential reading for all aeronautical engineers, mechanical engineers, mathematicians, and physicists.

Stewartson's theory for axisymmetric hypersonic flow of a model gas over slender bodies with strong viscous interaction and strong shock wave is extended to power-law viscosity variation and Prandtl numbers other than by: In addition, the book presents useful equations for calculating heat transfer between reacting gas boundary layers and reacting, melting, sublimating, and otherwise decomposing surfaces.

Designed for advanced undergraduate and graduate engineering courses in modern boundary-layer theory, this volume also serves as a valuable reference for. An analytical formulatton of the problem of hypersonic viscous interaction on a very slender body of revolution with a thick boundary layer and mass transfer is attempted.

Particular attention is directed to the establishment of the mathematical restrictions necessary to ensure the existence of similar solutions of the laminar boundary layer equa-File Size: KB. Cheng (), expanding on the difficulties in predicting viscous/inviscid interations, stated that, “the fluid dynamics of hypersonic flows is complicated by the interaction of the boundary layer and the shear layer with shock waves, leading to flow separation and instability not amenable to straightforward analysis.” Many of these flow Cited by: Viscous Shock Layer Vladimir V.

Riabov" Worcester Polytechnic Institute, Worcester, Massachusetts and Andrei V. Botint Central Aerohydrodynamics Institute, Zhukovsky-3, Moscow RegionRussia Different models of hypersonic diffusive hydrogen combustion in a thin viscous shuck layer (TVSL) at moderate.

Parameters of flow in a shock layer is obtained in approach of a viscous shock layer by numerical computation and with help of the physical and chemical models submitted in work.

Thus Reynolds’s number—Re ∞ varied (due to change of density of an external flow) from 5 × 10 3 to × 10 : Yuriy D. Shevelev. Title from cover. This banner text can have markup. web; books; video; audio; software; imagesPages:.

Get this from a library! Super- and Hypersonic Aerodynamics and Heat Transfer. [V Z Parton] -- "Recent government and commercial efforts to develop orbital and suborbital passenger and transport aircraft have resulted in a burgeoning of new research.

The articles in this book, translated from.Super- and hypersonic aerodynamics and heat transfer. Boca Raton, Fla.: CRC Press, © (DLC) (OCoLC) Material Type: Document, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: G K Mikhaĭlov; V Z Parton.This leads to merging of shock wave with boundary layer, constituting a ‘fully viscous shock layer’.

Shock wave angle is very small in this case. Hence large change in pressure density and velocity is experienced across this shock layer. Entropy layer In this flow regime, the thin shock waves curves downstream of the vehicle and wraps.