Viscous-shock-layer Analysis of Hypersonic Flows Over Long Slender Vehicles
Author : Kam-Pui Lee
Publisher :
Page : 226 pages
File Size : 26,6 MB
Release : 1992
Category : Fluid mechanics
ISBN :
Author : Kam-Pui Lee
Publisher :
Page : 226 pages
File Size : 26,6 MB
Release : 1992
Category : Fluid mechanics
ISBN :
Author : E. V. Zoby
Publisher :
Page : pages
File Size : 16,37 MB
Release : 1988
Category :
ISBN :
Author : Stanley G. Rubin
Publisher :
Page : 85 pages
File Size : 15,88 MB
Release : 1967
Category :
ISBN :
The hypersonic viscous pressure interaction is treated by the development of a set of equations valid throughout the boundary layer, shock-wave structure and inviscid core. Primary interest is concerned with the nature of the leading edge continuum merged layer in which the shock wave and boundary layer are indistinguishable. Due to the parabolic nature of the equations, finite-difference solutions are attainable. The flow over a flat plate at zero incidence, as well as angle of attack, was considered. Velocity and state variable distributions across the viscous layer depict the formation of an outer shock wave and inner constant pressure boundary layer. The calculated values of surface pressure, heat transfer and shock jump conditions were at first significantly below the values predicted by strong interaction theory. Agreement was quite good downstream of the merged layer where Rankine-Hugoniot jump conditions were satisfied to within 8%. (Author).
Author :
Publisher :
Page : 1056 pages
File Size : 30,27 MB
Release : 1972
Category : Aeronautics
ISBN :
Author : Y.P. Golovachov
Publisher : Springer Science & Business Media
Page : 359 pages
File Size : 17,64 MB
Release : 2013-03-09
Category : Mathematics
ISBN : 9401584907
The book is concerned with mathematical modelling of supersonic and hyper sonic flows about bodies. Permanent interest in this topic is stimulated, first of all, by aviation and aerospace engineering. The designing of aircraft and space vehicles requires a more precise prediction of the aerodynamic and heat transfer characteristics. Together with broadening of the flight condition range, this makes it necessary to take into account a number of gas dynamic and physical effects caused by rarefaction, viscous-inviscid interaction, separation, various physical and chemical processes induced by gas heating in the intensive bow shock wave. The flow field around a body moving at supersonic speed can be divided into three parts, namely, shock layer, near wake including base flow, and far wake. The shock layer flow is bounded by the bow shock wave and the front and lat eral parts of the body surface. A conventional approach to calculation of shock layer flows consists in a successive solution of the inviscid gas and boundary layer equations. When the afore-mentioned effects become important, implementation of these models meets difficulties or even becomes impossible. In this case, one has to use a more general approach based on the viscous shock layer concept.
Author : Wallace D. Hayes
Publisher : Courier Corporation
Page : 628 pages
File Size : 13,6 MB
Release : 2012-07-13
Category : Science
ISBN : 0486160483
Unified, self-contained view of nonequilibrium effects, body geometries, and similitudes available in hypersonic flow and thin shock layer; appropriate for graduate-level courses in hypersonic flow theory. 1966 edition.
Author : E. Clay Anderson
Publisher :
Page : 44 pages
File Size : 29,64 MB
Release : 1975
Category : Aerodynamics, Hypersonic
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Author : V. S. Nikolaev
Publisher :
Page : 20 pages
File Size : 32,22 MB
Release : 1967
Category : Aerodynamics, Hypersonic
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Author :
Publisher :
Page : 752 pages
File Size : 19,65 MB
Release : 1994
Category : Government publications
ISBN :
Author :
Publisher :
Page : 572 pages
File Size : 21,8 MB
Release :
Category : Military research
ISBN :