Results 221 to 230 of about 9,153 (265)
Some of the next articles are maybe not open access.
Nature, 1946
DR. GRIFFIN has recently published1 some further observations on the cries of bats, which are of great interest. He demonstrates clearly that the pulse of sound is often extremely short, having a duration which usually does not exceed 2.3 milliseconds.
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DR. GRIFFIN has recently published1 some further observations on the cries of bats, which are of great interest. He demonstrates clearly that the pulse of sound is often extremely short, having a duration which usually does not exceed 2.3 milliseconds.
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Multi-objective optimization of supersonic-supersonic ejector
High Power Laser and Particle Beams, 2012For supersonic-supersonic ejector, the design model and corresponding analysis were presented, and the relation of design parameters and the performance was partly revealed. The results revealed the confliction of two performance objectives and the complexity of the design problem.
陈钦 Chen Qin +3 more
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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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Evolution of subsonic and supersonic corner vortices in a supersonic cascade
Aerospace Science and Technology, 2019Abstract Numerical investigations on a supersonic cascade are conducted at the flow-through, high-backpressure, and low-speed modes to obtain a deeper understanding of the generation, development, and transformation of the subsonic and supersonic corner vortices. The geometry considered is the SAV21 supersonic cascade designed by the German Aerospace
Ziao Wang +3 more
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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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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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Effect of the second-throat on the performance of supersonic-supersonic ejectors
Science China Technological Sciences, 2012The pressure matching and recovery performances of the second-throat supersonic-supersonic ejector have been performed experimentally and numerically in the current study. Schlieren pictures of flow structure in former part of the mixing chamber with varied stagnation pressure ratio of the primary and secondary flows have been taken, and the maximum ...
Jian Chen +3 more
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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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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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Mixing of a Heated Supersonic Jet with a Supersonic Parallel Stream
1995Compressible mixing layers have been investigated by several authors (see e.g. the reviews by Goebels & Dutton, 1990, Barre et al., 1994). Supersonic jets are less documented. However, experiments (e.g. Gutmark et al., 1991) and stability analysis (e.g.
L. Jacquin +3 more
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