Results 261 to 270 of about 138,816 (307)
Some of the next articles are maybe not open access.
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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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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Journal of the Aerospace Sciences, 1960
An approximation of the differential equation for compressible duct flow is presented. The equation is linear and of the second order. The duct transfer function and response characteristics are obtained by applying small-perturbation theory to the differential equation.
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An approximation of the differential equation for compressible duct flow is presented. The equation is linear and of the second order. The duct transfer function and response characteristics are obtained by applying small-perturbation theory to the differential equation.
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Journal of Spacecraft and Rockets, 1971
An analytical method is presented for the design of axisymmetric annular nozzles to yield uniform and axial flow. Computed results are used to display typical matched inner and outer contours, the effects of major initial flow variables, and the resulting wall forces.
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An analytical method is presented for the design of axisymmetric annular nozzles to yield uniform and axial flow. Computed results are used to display typical matched inner and outer contours, the effects of major initial flow variables, and the resulting wall forces.
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The Airworthiness of Supersonic Aircraft
The Aeronautical Journal, 1967SummaryThe safety target for the Supersonic Transport has been set by the governments sponsoring the project. This is to achieve a safety level at least as good as that of subsonic aircraft at the same time. An analysis of present accident trends is used to give more precision to this statement.
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2013 IEEE International Workshop on Genomic Signal Processing and Statistics, 2013
Bilal Wajid +6 more
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Bilal Wajid +6 more
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Supersonic transverse injection into a supersonic stream.
AIAA Journal, 1968JOSEPH A. SCHETZ +2 more
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Optimisation study of a supersonic separator considering nonequilibrium condensation behaviour
Energy Conversion and Management, 2020Chuang Wen, Hongbing Ding, Yan Yang
exaly