Results 261 to 270 of about 116,720 (315)

New Shock Detector for Shock-Boundary Layer Interaction

2010
Standard compact scheme or upwind compact scheme have high order accuracy and high resolution, but cannot capture the shock which is a discontinuity. This work developed a modified compact scheme by an effective shock detector to block compact scheme to cross the shock, a control function, and an adaptive scheme which uses some WENO flux near the shock.
Chaoqun Liu, Maria Oliveira 0001
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Analysis of Multiple Weak Glancing Shock/Boundary-Layer Interactions

AIAA Journal, 1980
An analysis is developed for the change in boundary-laye r properties across a system of weak glancing shock/boundary-layer interactions. For a control volume about a given interaction, integral continuity, crossstream momentum, and streamwise momentum equations are solved for the boundary-layer properties downstream of the interaction.
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On the Shock Boundary Layer Interaction in Transonic Compressor Blading

Volume 13A: Turbomachinery — Axial Flow Fan and Compressor Aerodynamics, 2023
Abstract Shock waves and their interaction with the boundary is a significant flow effect within transonic compressor blading. The main challenge here is the unsteady nature of this interaction effect because it imposes further requirements to maintain the structural integrity of the blading. Furthermore, it has been shown that the shock
Hergt, Alexander, Klose, Björn, Klinner, Joachim, Bergmann, Michael, Munoz Lopez, Edwin Joseph, Grund, Sebastian, Morsbach, Christian   +6 more
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Shock/Boundary Layer Interaction in Rarefied Flow

38th Fluid Dynamics Conference and Exhibit, 2008
NOMENCLATURE A = Airy Function Cx ,Cy ,Cu ,Cv ,Cπ ,Cd = Triple Deck Scaling Factors C = Constant in upstream solution (Eq. 24) G = Functional involving Airy function properties (Eq.
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Transpiration Induced Shock Boundary-Layer Interactions

Journal of Fluids Engineering, 2006
Steady and unsteady shock boundary-layer interactions are studied numerically by solving the two-dimensional time-dependent Navier-Stokes equations. To validate the numerical method, the steady interaction is compared with measurements and other numerical results reported in the literature.
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Investigation of oblique shock/boundary-layer bleed interaction

Journal of Propulsion and Power, 1992
The detailed flowfield characteristics in an oblique shock-wave/laminar-boundary-layer interaction with bleed were investigated. The numerical solution for the flowfield was obtained for the strong conservation-law form of the two-dimensional compressible Navier-Stokes equations using an implicit scheme.
A. Hamed, T. Lehnig
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Calculation of the length of the shock-boundary layer interaction zone

Fluid Dynamics, 1987
An analytic relation for determining the length of the shock-laminar or turbulent boundary layer interaction zone is obtained on the basis of an analysis of the boundary layer separation criterion. It is shown that as the Mach number of the flow increases, the interaction length decreases, and that with increase in the Reynolds number it behaves ...
T. I. Malik, R. K. Tagirov
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SIMULATION OF AEROELASTIC MESOFLAPS FOR SHOCK/BOUNDARY-LAYER INTERACTION

Journal of Fluids and Structures, 2002
Abstract A novel concept involving an array of mesoflaps that allow for aeroelastic recirculating transpiration has the capability to control shock/boundary-layer interactions. The concept consists of a matrix of small flaps (rigidly fixed at their upstream end and covering an enclosed cavity) which are designed to undergo aeroelastic deflection to ...
B. WOOD, E. LOTH, P. GEUBELLE
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Passive control of shock-boundary layer interaction

Progress in Aerospace Sciences, 1988
Abstract Passive control shock-boundary layer studies, both theoretical and experimental, are reviewed in this paper. The first paper in this area was published in 1983. Since then there have been programmes of research in U.S.A., Germany and U.K. to understand the concept of passive shock wave boundary layer control and to predict the effect of such
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On the lengthscales of laminar shock/boundary-layer interaction

Journal of Fluid Mechanics, 1989
The interaction of an oblique shock with a laminar boundary layer on an adiabatic flat plate is analysed by solving the Navier-Stokes equations numerically. Mach numbers range from 1.4 to 3.4 and Reynolds numbers range from 105 to 6 × 105. The numerical results agree well with experiments.
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