Results 11 to 20 of about 160,803 (161)
Some hypersonic intake studies [PDF]
, 2006 A 'two dimensional' air intake comprisipg a wedge followed by an isentropic compression has been tested in the Cranfield Gun Tunnel at Mach 8,2. These tests were performed to investigate qualitatively the intake flow starting process. The effects of cowl
Lanson, F., Stollery, J. L.
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Hypersonic flow control using magneto-hydrodynamics [PDF]
, 2008 The focus of the present work is on the use of magneto hydrodynamics as a flow control device for supersonic and hypersonic vehicles. A three dimensional parabolized Navier Stokes solver was developed to take into account the effects of magnetic ...
Bennett, J. S.
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Aerospace, 2022 The Reynolds number effect induced by model scaling and inflow conditions will affect the aerodynamic and starting characteristics of a two-dimensional hypersonic inlet. This effect is investigated through a numerical simulation method.
Jun Liu, Jingzhe Chen, Huacheng Yuan
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Lagrange Optimization of Shock Waves for Two-Dimensional Hypersonic Inlet with Geometric Constraints
Aerospace, 2022 The present paper focuses on the Lagrange optimization of shock waves for a two-dimensional hypersonic inlet by limiting the cowl internal angle and inlet length.
Yuling Li +4 more
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Effects of Configuration and Slot Angle of the Bleed System on the Performance of Hypersonic Inlet
气体物理, 2023 The numerical simulation of a typical two-dimensional hypersonic inlet was carried out to study the effects of configuration and slot angle of the bleed system on the performance of hypersonic inlet.
Hao-Yu CHEN, He-Xia HUANG, Hui-Jun TAN
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Experimental Investigation on the Influence of Yaw Angle on the Inlet Performance at Mach 7 [PDF]
, 2010 This paper presents the results of an extensive measurement campaign that was conducted with an two-dimensional hypersonic inlet in the Hypersonic Windtunnel H2K at the German Aerospace Center in Cologne in order to study the effects of angle of yaw on ...
Ali Gülhan +3 more
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Hypersonic control effectiveness
, 1995 The present study analyses the effects of a number of geometric parameters on the performance of a trailing edge control flap on a hypersonic body. The tests were conducted in a gun tunnel at Mach 8.2 and Mach 12.3.
Kumar, D.
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Assessment of Total Pressure and Swirl Distortions in a Busemann Inlet at Mach 6 [PDF]
Journal of Applied Fluid Mechanics, 2023 Flow distortions in high-speed inlet systems are complex, and high-performance air-breathing propulsion systems. In this paper, large eddy simulations are performed to study the total pressure and swirl distortions in a Busemann inlet at freestream Mach ...
Y. Li, Z. Wu, S. Wu, S. Hu, F. Wei
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Analysis of a Three-Dimensional, High Pressure Ratio Scramjet Inlet with Variable Internal Contraction [PDF]
, 2012 We conducted an extensive experimental examination of the operational behavior of a three-dimensional scramjet inlet featuring a movable cowl to adapt the internal contraction according to the respective operation conditions.
Hohn, Oliver +3 more
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Experimental Investigation on the Influence of Sidewall Compression on the Flowfield of a Scramjet Inlet at Mach 7 [PDF]
, 2011 In this paper, we present the results of an extensive measurement campaign to investigate the effect of external and internal sidewall compression as well as different contraction ratios on the performance of the flowfield of a scramjet inlet ...
Ali Gülhan +3 more
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