Results 221 to 230 of about 4,685 (268)
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1947
This thesis is a presentation of the methods and concepts of the theory of linearized supersonic flow. The fundamental theory which serves as a basis for this investigation is discussed in the first two chapters. Special emphasis is placed upon the study of planar systems. A system of conical coordinates is introduced in which the method of separation
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This thesis is a presentation of the methods and concepts of the theory of linearized supersonic flow. The fundamental theory which serves as a basis for this investigation is discussed in the first two chapters. Special emphasis is placed upon the study of planar systems. A system of conical coordinates is introduced in which the method of separation
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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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Control of Supersonic Cavity Flow
2012In this study, laser energy deposition is used as a flow control technique. The effects of laser energy deposition over an open rectangular supersonic cavity flow to realize the capability of the energy deposition for reduction of the pressure fluctuations and relative sound pressure levels are examined numerically.
Ayli, Ece +2 more
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Supersonic Flow Over Axisymmetric Cavities
37th AIAA Fluid Dynamics Conference and Exhibit, 2007Laminar and turbulent computations of rectangular cavities in Mach 2.2 flow are presented. Unsteady open cavities are shown in all laminar cases (L/D = 1.33, 10.33, 11.33 and 12.33) whilst turbulent simulations exhibit closed cavity flows for L/D of 11.33 and 12.33. The turbulent computations are supported by experimental schlieren images using a spark
Mohri, Khadijeh, Hillier, Richard
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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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Flow Characteristics of a Supersonic Open Cavity
Fluid Dynamics, 2019zbMATH Open Web Interface contents unavailable due to conflicting licenses.
Wang, J. M. +4 more
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Measures of intermittency in driven supersonic flows
Physical Review E, 2002Scaling exponents for structure functions of the velocity, density, and entropy are computed for driven supersonic flows for rms Mach numbers of order unity, with numerical simulations using the piecewise parabolic method algorithm on grids of up to 512(3) points. The driving is made up of either one or three orthogonal shear waves.
D, Porter, A, Pouquet, P, Woodward
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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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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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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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