Results 211 to 220 of about 4,685 (268)
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The Flow of a Supersonic Jet in a Supersonic Stream at an Angle of Attack
Journal of the Aerospace Sciences, 1958where M is the Mach Number, P the pressure, and the subscripts, 1 and 2, refer to the jet stream and the exterior flow, respectively. If k = 1, for two dimensions there are no reflections from the jet interface and the jet aligns itself with the original undisturbed flow in a finite distance.
Ehlers, F. Edward, Strand, Torstein
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Journal of Applied Physics, 1949
For a definite Mach number, given by M2 = 4/(3−γ), all Mach lines in a steady plane two-dimensional potential flow of a perfect gas with expansion exponent γ have zero curvature. The use and significance of this relation are discussed, and the hypothetical expansion law consistent with straight Mach lines is deduced.
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For a definite Mach number, given by M2 = 4/(3−γ), all Mach lines in a steady plane two-dimensional potential flow of a perfect gas with expansion exponent γ have zero curvature. The use and significance of this relation are discussed, and the hypothetical expansion law consistent with straight Mach lines is deduced.
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2022
The nozzle flow is considered to be much more important in aerospace applications. Based on the pressure, velocity and temperature, flow velocity, Mach number and area, the nozzle shape will vary to meet the required condition. Nozzle is a part where the potential energy is converted into kinetic energy.
Nithya Subramani +3 more
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The nozzle flow is considered to be much more important in aerospace applications. Based on the pressure, velocity and temperature, flow velocity, Mach number and area, the nozzle shape will vary to meet the required condition. Nozzle is a part where the potential energy is converted into kinetic energy.
Nithya Subramani +3 more
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Progress in Aerospace Sciences, 1974
Abstract This report gives a survey of the inviscid supersonic flow through a straight lattice row. The main subject of this paper is dedicated to the supersonic inlet and outlet flow at such a cascade. It is shown that the cascade flow behaviour is altered radically when the axial velocity component changes from supersonic to subsonic velocities or ...
H.-J. Lichtfuss, H. Starken
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Abstract This report gives a survey of the inviscid supersonic flow through a straight lattice row. The main subject of this paper is dedicated to the supersonic inlet and outlet flow at such a cascade. It is shown that the cascade flow behaviour is altered radically when the axial velocity component changes from supersonic to subsonic velocities or ...
H.-J. Lichtfuss, H. Starken
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Combustion, Explosion and Shock Waves, 1987
Examples of numeric modeling of complex combustion processes in supersonic flows are presented which illustrate the possibility of obtaining useful information which may reveal their basic regularities determined by the parameters of the entrance streams, mode of injection, type of fuel, and the interaction of various factors pertaining to combustion ...
V. K. Baev +2 more
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Examples of numeric modeling of complex combustion processes in supersonic flows are presented which illustrate the possibility of obtaining useful information which may reveal their basic regularities determined by the parameters of the entrance streams, mode of injection, type of fuel, and the interaction of various factors pertaining to combustion ...
V. K. Baev +2 more
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On the structure of supersonic flow
ZAMP Zeitschrift für Angewandte Mathematik und Physik, 1958Die im Grossen invarianten Eigenschaften von Wellenfronten, Zweig- und Grenzlinien in der ebenen, stetigen, wirbelfreien und isentropischen Stromung idealer Gase werden diskutiert.
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Flow Dominating Instability in Supersonic Flows
2020The shock-induced separation is a common phenomenon in supersonic combustion, especially when the scramjet combustor works under high equivalence ratios. The low-speed recirculation zone and strong heat release enable the separated region to be an ideal place for flame stabilization.
Mingbo Sun +3 more
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Spectral Simulation of Supersonic Reactive Flows
SIAM Journal on Numerical Analysis, 1998The authors present a Chebyshev collocation scheme for the numerical simulation of reactive flows with shock waves. It is shown that spectral methods are suitable for the numerical approximation of reactive flows interacting with shock waves. Theoretical and numerical results on interactions of hydrogen jets with shock waves are analyzed, and ...
Don, Wai Sun, Gottlieb, David
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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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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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