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• W2325442078 abstract "The nonlinear evolution of the second mode disturbance across a compression corner under the hypersonic flow condition is studied by spatial direct numerical simulation in this investigation. A fifth-order weighted essentially non-oscillating(WENO) scheme is employed for this simulation. After the mean flow is obtained, the twoand threedimensional monoor random-frequency disturbances are added into the mean flow at the beginning of the computational domain. The nonlinear simulations show that twodimensional disturbance will become saturated downstream of the separation region when its amplitude grows to a quite large value. For three-dimensional mono-frequency disturbance evolution, with appropriate initial disturbance amplitude, the nonlinear interactions of the oblique disturbance will first happen at the beginning of the separation region and some super-harmonics will begin to appear in this region, but only downstream of the separation region do these harmonics begin to grow rapidly. Among all these superharmonics, (0,2) mode shows the greatest growth rate and is responsible for oblique breakdown. With the presence of the twodimensional primary disturbance, the oblique disturbances show the significant growth rate downstream of the separation region when the two-dimensional primary disturbance reaches the nonlinear saturation. Both monoand random-frequency disturbance evolution show that the growth of the fundamental harmonic is responsible for the boundary-layer transition. Introduction In this investigation, spatial direct numerical simulation is employed to study the nonlinear evolution of the second mode disturbance in the hypersonic boundary layer across a compression corners. As we know, when a large adverse pressure gradient exists in the inviscid pressure distribution, the viscous effects become important. The interaction of the boundary layer and the pressure gradient modifies the pressure distribution and the flow field is drastically modified including multiple shocks, flow separation, transition to turbulence, unsteadiness and three-dimensionality. These phenomena are observed in the experiments of transonic flow over airfoils by Ackert, Feldmann and Rott, supersonic flows over 12th AIAA International Space Planes and Hypersonic Systems and Technologies 15 19 December 2003, Norfolk, Virginia AIAA 2003-7066 Copyright © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. compression corners, bases and steps by Chapman, Kuehn and Larson. It can be seen from these experiments that the flow separates some distance upstream the shock impingement point and a separation bubble forms across the shock on the wall surface. And the transition location has a significant influence on the pressure distribution along" @default.
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• W2325442078 date "2003-12-15" @default.
• W2325442078 modified "2023-10-16" @default.
• W2325442078 title "Direct Numerical Simulation of Nonlinear Disturbance Evolution Across a Hypersonic Compression Corner" @default.
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• W2325442078 doi "https://doi.org/10.2514/6.2003-7066" @default.
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