Results 221 to 230 of about 4,511 (269)
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British Journal of Applied Physics, 1954
An introduction to supersonic gas flow is given, with emphasis on the features that distinguish supersonic from subsonic flow. Experimental methods for the study of supersonic flow are briefly considered and some simple flows are described.
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An introduction to supersonic gas flow is given, with emphasis on the features that distinguish supersonic from subsonic flow. Experimental methods for the study of supersonic flow are briefly considered and some simple flows are described.
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Flow Field Study of a Supersonic Jet Exiting into a Supersonic Stream
2006The paper present a numerical/experimental investigation of the flow field resulting around a generic vehiole controlled by means of a lateral jet in supersonic motion. The experimental data are acquired in the DLR wind tunnel TMK in Cologne. To obtain the numerical results, the 3-D viscous, turbulent, Reynolds-averaged hybrid Navier-Stokes Code TAU of
Adeli, R., Longo, J.M.A., Emunds, H.
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2010
Compressible flow past thin wings and slender bodies are studied. First, subsonic flow past thin wings are analyzed by means of potential flow theory. The kernel function method is introduced for arbitrary planforms undergoing simple harmonic oscillations.
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Compressible flow past thin wings and slender bodies are studied. First, subsonic flow past thin wings are analyzed by means of potential flow theory. The kernel function method is introduced for arbitrary planforms undergoing simple harmonic oscillations.
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A Computational Method for Combustion in Supersonic Flows
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011A numerical technique to solve two-dimensional reacting ow eld in chemical nonequilibrium is presented. The aim of this study is to develop a computational tool which permits the analysis of combustion phenomena at high speed ows. The numerical approach is based on a time-dependent, nite-volume integration of the Euler equations suitably modi ed for ...
FERRAT, CHRISTIAN, MARSILIO, Roberto
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Tangential slot injection in supersonic flow.
AIAA Journal, 1967The flowfield associated with tangential slot injection of a gas into a supersonic external stream is of current technological and academic interest. The present study can be divided into three areas. First, detailed profiles in the near flowfield were determined with an interferometer for air injection into a Mach 2.1 airstream past a flat plate ...
H. GILREATH, J. SCHETZ
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2019
The present chapter treats supersonic flows and shock fronts (also termed shock waves or simply shocks). A shock is an enduring and smooth surface in a fluid through which the fluid passes; in this passage, the fluid density, pressure, velocity, and temperature all undergo abrupt changes (‘jumps’).
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The present chapter treats supersonic flows and shock fronts (also termed shock waves or simply shocks). A shock is an enduring and smooth surface in a fluid through which the fluid passes; in this passage, the fluid density, pressure, velocity, and temperature all undergo abrupt changes (‘jumps’).
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Vortical solutions in supersonic corner flows
31st Aerospace Sciences Meeting, 1993Vortical solutions are investigated for inviscid supersonic steady flows, described by the steady-state Euler equations, that occur in the corner region generated by two orthogonal ramps. Complex shock interactions appear, with the formation of a vorticity field in the corner region and the vorticity itself converging into spiral singularities ...
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On wing–body interference in supersonic flow
Mathematika, 1966Although the theory of supersonic inviscid flow past thin wings and slender bodies has received an enormous amount of attention in recent years, comparatively little attention has been paid to the interaction between wings and finite bodies. The principal reason stems from the extensive numerical work that has to be done in order to form a detailed ...
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Supersonic Flow With Variable Specific Heat
Journal of Applied Mechanics, 1952Abstract Formulas are developed for stagnation conditions and one-dimensional flow through shock waves, including Rankine-Hugoniot values, taking into account the variation of the specific heat of air with temperature by means of the concept of mean specific heats.
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On Supersonic Flow Past Thick Airfoils
Journal of the Aerospace Sciences, 1960= = = = = — speed of sound, in units of limiting velocity pressure coefficient airfoil profile undisturbed-flow Mach number pressure gas constant entropy temperature Cartesian coordinates velocity components in x and y directions, in units of limiting velocity velocity, in units of limiting velocity ratio of specific heats flow inclination to ...
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