Published 1993 by Dept. of Aerospace Engineering Sciences, University of Colorado, National Aeronautics and Space Administration, National Technical Information Service, distributor in Boulder, Colo, [Washington, D.C, Springfield, Va .
Written in EnglishRead online
|Other titles||Numerical simulation of shock, turbulent boundary layer interaction.|
|Statement||principal investigator, Sedat Biringen.|
|Series||NASA contractor report -- NASA CR-198846.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Download Numerical simulation of shock/turbulent boundary layer interaction
Direct numerical simulation of the Navier–Stokes equations is carried out to investigate the interaction of a conical shock wave with a turbulent boundary layer developing over a flat plate at. Jun 21, · A direct numerical simulation of the shock/turbulent boundary layer interaction flow in a supersonic degree compression ramp is conducted with the Cited by: Jun 13, · In this paper, direct numerical simulations are performed to study the interactions of shock waves with a supersonic turbulent boundary layer in compression corners with different turning angle.
Accuracies of this DNS are validated by comparison with pervious simulation and experimental data, and the effects of turning angle are evaluated. (1)Cited by: 3. ﬂare experiments were selected to analyze the shock/boundary layer interaction behavior, namely the size of the separated region, the proﬁles of mean velocity and turbulence quantities downstream of the shock, and the quality of the prediction of surface pressure, skin friction and heat transfer in the recovering boundary layer.
An Implicit Large Eddy Simulation of a Mach reflected oblique shock/turbulent boundary layer interaction (Reθ =generated by a 9° wedge) is employed to understand the dynamics of the. ibility effects in turbulent, high-speed, boundary layer flows are systemati-cally investigated using the Direct Numerical Simulation (DNS) approach.
Three-dimensional, time-dependent, fully nonlinear, compressible Navier-Stokes equations were numerically integrated by high-order finite-difference. Direct numerical simulation of turbulent boundary-layer flow over a circular-arc bump including shock/boundary-layer interactions has been carried out at Reynolds number Re δ 1 * = (based on the stagnation quantities and the inflow displacement thickness).
The compressible Navier-Stokes equations were solved in generalized coordinates using a 4th-order central finite-difference-TVD Cited by: 4. May 01, · Numerical simulations have been captured for 3-D crossing shock wave/turbulent boundary layer interactions generated by deg sharp fins mounted symmetrically on a flat plate at mach The full Reynolds-averaged Navier-Stokes equations are solved with high-resolution implicit finite-volume birminghamasphaltcontractor.com: Wei Xuan Kong, Peng Zeng, Chao Yan, Rui Zhao.
The large eddy simulation (LES) of a compression ramp shock wave and turbulent boundary layer interaction (STBLI) is presented. The ramp angle is 24 and the incoming boundary layer ow conditions are Mach and Re The LES data are in good agreement with existing direct numerical simulation (DNS) data with the same incoming ow parameters.
Investigation of 3D Shock-Boundary Layer Interaction: A Combined Approach using Experiments, Numerical Simulations and Stability Analysis Jesse Little and Hermann Fasel University of Arizona Andreas Gross New Mexico State University AFOSR AT and T2 Numerical simulation of shock/turbulent boundary layer interaction book.
July 15, 1. Get this from a library. Numerical simulation of shock/turbulent boundary layer interaction: final year report for NASA grant NAG [Sedat Biringen; United. Results of numerical simulation of interaction between an oblique shock wave and a turbulent boundary layer formed in a supersonic (Mach number M =5) flow past a flat plate are presented.
The computations are performed for three cases of interaction of different Cited by: Center for Turbulence Research Proceedings of the Summer Program Large-eddy simulation of shock/boundary-layer interaction By A.
Hadjadj†, J. Larsson, B. Morgan, J. Nichols AND S. Lele This work considers numerical simulations of supersonic ﬂows when shock/turbulent.
Abstract: A transonic interaction between a shock wave and a turbulent boundary layer is experimentally and theoretically investigated.
The configuration is a transonic channel flow over a bump, where a shock wave causes the separation of the boundary layer in the.
The numerical simulation of turbulent hypersonic flows poses a number of significant challenges. Chief among these challenges is the stringent grid resolution requirement in the boundary layer to accurately predict wall heat ux and skin birminghamasphaltcontractor.com by: 4.
Mar 10, · An experimental study is carried out to investigate the three-dimensional instantaneous structure of an incident shock wave/turbulent boundary layer interaction at Mach using tomographic particle image birminghamasphaltcontractor.com by: Aug 30, · Interaction between a weak oblique shock wave and a turbulent boundary layer in purely supersonic flow Acta Mechanica, Vol.
53, No. Numerical simulation of 3-D shock-turbulent boundary layer interaction generated by a sharp finCited by: ILES has been performed for the compression ramp case at moderate Reynolds numbers of ×, based on the boundary layer thickness, and compared to Direct Numerical Simulations (DNS).
AB - An investigation of the accuracy of high-order methods for hypersonic shock wave turbulent boundary layer interaction (SWTBLI) is birminghamasphaltcontractor.com by: 7. Jul 12, · Interaction between a shock wave and an unseparated turbulent boundary layer is considered.
The method of matched asymptotic expansions is used, with solutions valid in the double limit as Reynolds number tends to infinity and Mach number tends to birminghamasphaltcontractor.com by: The numerical simulations directly reproduce an available experiment.
The compression ramp has a deflection angle of β= 25°. The mean free-stream Mach number is M∞ = The Reynolds number based on the incoming boundary-layer thickness is Reδ 0 Cited by: Numerical study of boundary layer separation control using magnetogasdynamic plasma actuators.
Numerical simulation of flow separation in rocket nozzle. Mechanics Research Communications, Vol. 24, No. 3 Transonic shock-turbulent boundary layer interaction with suction and blowing.
INGER;Cited by: Mach 5 Shock Wave Boundary Layer Interaction: Study #1 Case Files. The following tar file is a complete package of grids, solutions, pre- and post-processing scripts, and experimental data used during the course of this validation study.
Interaction between a shock wave and an unseparated turbulent boundary layer is considered. The method of matched asymptotic expansions is used, with solutions valid in the double limit as Reynolds number tends to infinity and Mach number tends to unity.
The shock is weak enough that interaction effects can be considered as perturbations to the undisturbed flow; the case considered is that Cited by: The need for better understanding of the low-frequency unsteadiness observed in shockwave/turbulent boundary layer interactions has been driving research in this area forseveral decades.
This work investigates the interaction between an impinging obliqueshock and a supersonic turbulent boundary layer via large-eddy simulations. Shen, Y., Zha, G. ().Large Eddy Simulation Using a New Set of Sixth Order Schemes for Compressible Viscous Terms.
Journal of Computational Physics,Wang, W., Zha, G. ().Numerical Simulation of Transonic Limit Cycle Oscillations Using High Order Low Diffusion Schemes.
Journal of Fluids and Structures, unkoown, unknown. Get this from a library. Computation and Comparison of Efficient Turbulence Models for Aeronautics - European Research Project ETMA.
[Alain Dervieux; Marianna Braza; Jean-Paul Dussauge] -- The computation of complex turbulent flows by statistical modelling has already a long history. The most popular two-equation models today were introduced in the early sev enties.
Jan 22, · Mach 5 Shock Wave Boundary Layer Interaction. Figure 1: Flowfield. Introduction. This case was performed to validate the unstructured algorithm of Wind-US code. The validation focuses on a Mach 5 Shock Wave Boundary-Layer Interaction (SWBLI) designed after the work performed by Schulein et al.
of the German Aerospace Center (DLR). Modelling shock/turbulent-boundary-layer interaction with a cell-vertex scheme and second-moment closure. Pages Numerical simulation of non-equilibrium hypersonic flow using the second-order boundary layer equations. Book Title Twelfth International Conference on Numerical Methods in.
Boundary Layer Influence on Supersonic Jet/Cross-Flow Interaction in Hypersonic Flow M. Havermann, F. Seiler.
Numerical Rebuilding of a Generic Body-Flap Model in an Arc Heated Facility A. Mack, M. Emran, R. Schäfer. Experimental and Numerical Investigations of Shock/Turbulent Boundary Layer Interaction on a Double Ramp Configuration.
New Results in Numerical and Experimental Fluid Mechanics V aeroelasticity, aeroacoustics, mathematical fundamentals/ numerical simulation, physical fundamentals, and facilities. Experimental and Numerical Investigations of Shock/Turbulent Boundary Layer Interaction on.
Knight, D., ``Numerical Simulation of a Three-Dimensional Shock Wave-Turbulent Boundary Layer Interaction Generated by a Sharp Fin at Mach 4'', Computing Systems in Engineering, 1, Nos.
The approximate deconvolution model for large-eddy simulation is formulated for a second-order finite volume scheme. With the approximate deconvolution model, an approximation of the unfiltered solution is obtained by repeated filtering, and given a good approximation of the unfiltered solution, the nonlinear terms of the Navier-Stokes equations are computed birminghamasphaltcontractor.com by: 8.
Numerical simulation results using large-eddy simulation of a flow configuration relevant to the film cooling of turbine blades are presented. The Approximate Deconvolution Model for Large-Eddy Simulations of Compressible Flows and Its Application to Shock-Turbulent-Boundary-Layer Interaction,” Direct Simulation of a Turbulent Cited by: Journal Publications.
Espinal, D., Im, H.-S. and Zha, G.-C. “Full-Annulus Simulation of Non-Synchronous Blade Vibration Excitation of an Axial Compressor” J.
Utilising a pragmatic, physical approach, this self-contained book provides a comprehensive description of the concept. Beginning with the basic properties and numerical methods, it then guides readers through to the most recent advances in applications to complex birminghamasphaltcontractor.com by: He also wishes to thank the authors of the first ever to be performed Large Eddy Simulation of swept/shock turbulent boundary layer interaction, for permitting him to use material from their study.
Finally, he expresses his warm thanks to his colleague Alexander Zheltovodov for his birminghamasphaltcontractor.com by: 6. The full text of this article hosted at birminghamasphaltcontractor.com is unavailable due to technical birminghamasphaltcontractor.com by: An Upwind Scheme for Oblique Shock/Boundary Layer Interaction in a Supersonic Inlet p.
Calculation of a Viscous Hypersonic Nozzle Flow by a Second Order Implicit Scheme on Unstructured Meshes p. Shock-Boundary Layer Interaction by Shock Fitting p. Numerical Simulation of Supersonic Mixing Layer Using a Solution Adaptive. LIST OF PUBLICATIONS Journal Papers 1. W.S. Wong, N. Qin, N.
Sellars, H. Holden, H. Babinsky, A combined experimental and numerical study of flow structures over three-dimensional shock control bumps, Aerospace Science and Technology, 12,pp– 2.
N Qin, H Xia Detached eddy simulation of a synthetic jet for flow control. Proc. Lien F‑S and Leschziner M A (), Modelling shock / turbulent boundary‑layer interaction with second‑moment closure within a pressure‑velocity strategy, Proc. 13th Int. Conf. on Numerical Methods in Fluid Dynamics, Rome, Italy, July.
Full text of "Interferometric data for a shock-wave/boundary-layer interaction" See other formats.You can write a book review and share your experiences. Other readers will always be interested in your opinion of the books you've read.
Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.LIST OF PUBLICATIONS Patents 1. Howell R, Durrani N, Hamada K, Smith T, Unsteady flow simulation and dynamic stall behaviour of vertical axis wind turbine blades, Wind Engineering 35 (4), Grid adaptation for shock/turbulent boundary layer interaction.
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