Results 171 to 180 of about 8,165 (229)
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AIAA Journal, 1970
Abstract : A study of the motions of solid particles in a dusty gas in the inviscid hypersonic shock layers of slender wedges and cones and the stagnation regions of cylinders and spheres is carried out. Particles of uniform size and with a size distribution are considered.
RONALD F. PROBSTEIN, FRANCO FASSIO
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Abstract : A study of the motions of solid particles in a dusty gas in the inviscid hypersonic shock layers of slender wedges and cones and the stagnation regions of cylinders and spheres is carried out. Particles of uniform size and with a size distribution are considered.
RONALD F. PROBSTEIN, FRANCO FASSIO
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Panel flutter in hypersonic flow.
AIAA Journal, 1967IV," Transactions of the American Society for Metals, Transactions Quarterly, Vol. 59, 1966, p. 876. Fager D. N. and Spur W. F., "Some Characteristics of Aqueous Stress Corrosion in Titanium Alloys," Document D660083, Sept. 1967, The Boeing Co. 11 Beck, T. R., "Stress Corrosion Cracking of Titanium Alloys, II.
Bailie, J. A., McFeely, J. E.
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Physics Bulletin, 1959
By W. D. Hayes and R. F. Probstein New York and London: Academic Press Inc. Pp. xiv + 464. Price 92s. The book is directed to students and research workers in the field of modern gas-dynamics and to hypersonic aerodynamicists. The authors divide the hypersonic features of a high speed flow into those of a " hydrodynamic " nature which arise because the
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By W. D. Hayes and R. F. Probstein New York and London: Academic Press Inc. Pp. xiv + 464. Price 92s. The book is directed to students and research workers in the field of modern gas-dynamics and to hypersonic aerodynamicists. The authors divide the hypersonic features of a high speed flow into those of a " hydrodynamic " nature which arise because the
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Nonequilibrium hypersonic inviscid steady flows
AIAA Journal, 1992Summary: A numerical method for the solution of nonequilibrium flows about blunt bodies is presented. The method is based on the splitting in two parts of the reactive Euler equations: the gasdynamic operator (mass and momentum equations) and the chemical operator (energy and species conservation equations).
VALORANI, Mauro +3 more
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Design Optimization in Hypersonic Flows
18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012The objective of this study is to develop a reliabl e and efficient design tool that can be used in hyp ersonic flows. The flow analysis is based on axisymmetric Euler an d the finite rate chemical reaction equations. Thes e coupled equations are solved by using Newton’s method.
Eyi, Sinan, Yumuşak, M.
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2015
Abstract The chapter starts its analysis with blunt-nosed bodies. In a supersonic flow, a blunt-nosed body produces a bow shock wave. The chapter shows that the shape of the shock and the entire flow between the shock and the body become independent of the Mach number, M∞, provided it is large enough.
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Abstract The chapter starts its analysis with blunt-nosed bodies. In a supersonic flow, a blunt-nosed body produces a bow shock wave. The chapter shows that the shape of the shock and the entire flow between the shock and the body become independent of the Mach number, M∞, provided it is large enough.
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Nonequilibrium hypersonic flows over corners
AIAA Journal, 1991The hypersonic nonequilibrium flow of air over concave and convex corners is investigated. The description of the flowfield is based on the Euler equations and a chemical model that accounts for the finite rate reactions. An upwind formulation and the related space-marching technique are developed in order to achieve the numerical solution of the fluid
M. PANDOLFI, ARINA, RENZO, N. BOTTA
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1969
At hypersonic Mach numbers, significant pressures are induced on aerodynamic surfaces by both viscosity and bluntness effects. Viscosity-induced pressures are caused by the growth of the boundary layer. They are accounted for in the manner proposed by Prandtl (1) many years ago when he suggested taking the computed boundary-layer displacement thickness
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At hypersonic Mach numbers, significant pressures are induced on aerodynamic surfaces by both viscosity and bluntness effects. Viscosity-induced pressures are caused by the growth of the boundary layer. They are accounted for in the manner proposed by Prandtl (1) many years ago when he suggested taking the computed boundary-layer displacement thickness
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Nature, 1960
Hypersonic Flow Theory By Wallace D. Hayes and Ronald F. Probstein. (Applied Mathematics and Mechanics, Vol. 5. Series of Monographs prepared under the auspices of the Applied Physics Laboratory, The Johns Hopkins University.) Pp. xiv + 464. (New York: Academic Press, Inc.; London: Academic Press, Inc. (London), Ltd., 1959.) 11.50 dollars.
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Hypersonic Flow Theory By Wallace D. Hayes and Ronald F. Probstein. (Applied Mathematics and Mechanics, Vol. 5. Series of Monographs prepared under the auspices of the Applied Physics Laboratory, The Johns Hopkins University.) Pp. xiv + 464. (New York: Academic Press, Inc.; London: Academic Press, Inc. (London), Ltd., 1959.) 11.50 dollars.
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Two−dimensional hypersonic magnetohydrodynamic flow
The Physics of Fluids, 1975The problem of the two−dimensional, inviscid, infinitely−conducting hypersonic flow past nonconducting bodies, in the presence of near−aligned magnetic fields, is analyzed, the problem being solved by transforming from the physical plane to the stream function, magnetic stream function plane.
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