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Thursday, May 14, 2020 | History

3 edition of Turbulence modeling in shock wave/turbulent boundary layer interactions found in the catalog.

Turbulence modeling in shock wave/turbulent boundary layer interactions

Turbulence modeling in shock wave/turbulent boundary layer interactions

final report

  • 243 Want to read
  • 33 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Boundary layer noise.

  • Edition Notes

    Statementby A.J. Smits.
    SeriesNASA-CR -- 190933., NASA contractor report -- NASA CR-190933.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15367335M

      [26] Knight D. D. and Degrez G., “ Shock Wave Turbulent Boundary Layer Interactions in High Mach Number Flows: A Critical Survey of Current Numerical Prediction Capabilities,” NATO, Advisory Group for Aerospace Research and Development (AGARD), Advisory Rept. , Vol. 2, , pp. – Google ScholarCited by: 2. Garrison T J, Settles G S, Narayanswami N, Knight D D. Measurements of the triple shock wave turbulent boundary-layer interaction. AIAA Journal Garrison T J, Settles G S, Narayanswami N, Knight D D. Structure of crossing-shock-wave turbulent .

    Assessment of Shock and Boundary Layer Control - A Summary.- Overall Conclusions and Future Work.- Introduction to the Individual Contributions.- Study of Control Devices Applied to a Transonic Shock Wave/Boundary Layer Interaction.- Hybrid and Active Control of Shock Wave - Turbulent Boundary Layer Interaction and Perforated Plate.   Particularly, shock wave / turbulent boundary layer interactions (SWTBLI) in the vicinity of an asymmetric sharp double-fin (DF) with different (7° and 11°) deflection angles mounted on a flat plate and two conically sharp cylindrical bodies at varying interbody distances and nose cone angles 60° and 40° mounted over a flat platemore».

    @article{osti_, title = {Numerical studies of supersonic/hypersonic combustion}, author = {Yoon, W.S. and Chung, T.J.}, abstractNote = {This paper is concerned with the development of direct numerical simulations of turbulence interacting with shock waves and chemical reactions using unstructured adaptive finite element h-p methods. Investigation of small surface protuberances upstream of turbulent boundary layer separation produced by a skewed shock wave at Mach 3 / (Wright-Patterson Air Force Base, Ohio: Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Syspems Command, ), by Robert H Korkegi and Air Force Aero Propulsion.


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Turbulence modeling in shock wave/turbulent boundary layer interactions Download PDF EPUB FB2

Turbulence Modeling for Shock Wave/Turbulent Boundary Layer Interactions [Lillard, Randolph P., National Aeronautics and Space Administr] on *FREE* shipping on qualifying offers. Turbulence Modeling for Shock Wave/Turbulent Boundary Layer InteractionsCited by: 4. prediction of shock-wave/turbulent-boundary-layer interaction (SWTBLI) is pro vided by the side-load phenomenon in rocket nozzles (e.g.

Hagemann, F rey & Kosc hel ) which is responsible for. Horstman C.C. () Turbulence Modeling for Sharpfin-Induced Shock Wave/Turbulent Boundary-Layer Interactions. In: Kozlov V.V., Dovgal A.V. (eds) Separated Flows and Jets. International Union of Theoretical and Applied by: 2. Abstract. In this paper computational results for two different types of shock wave/turbulent boundary layer interaction flows are presented.

It is shown that upstream effects of the shock induced separation cannot be reproduced by Wilcox’s () k-ω-model, whereas downstream of the interaction, predictions of pressure distribution and skin friction are by: 9.

Navier-Stokes and Experimental Modeling of Blunt-Base Rocket Nozzle Flow.- Session 4 Interactions in Three-Dimensional Steady Flows Chairman: E. Krause.- A "Preview" of Three-Dimensional Shock-Wave/ Turbulent Boundary-Layer Interactions(*).- On the Inception Lengths of Swept Shock-Wave/ Turbulent Boundary-Layer Interactions Get this from a library.

Turbulence modeling in shock wave/turbulent boundary layer interactions: final report. [Alexander J Smits; United States. National Aeronautics and Space Administration.]. The paper presents a summary of recent computational fluid dynamics (CFD) simulations of shock wave turbulent boundary layer interactions.

This survey was prepared as part of the activity of NATO. The aim of the symposium was to provide an updated status of the research effort devoted to shear­ layer/shock-wave interactions and to present the most significant results obtained recently.

Show all. Present investigation deals with the interaction of an incident oblique shock wave on a turbulent boundary layer over a wavy surface.

The oblique shock wave was generated by an 8 deg wedge in a freestream Mach number of Cited by: 1. The reasons for the difficulty in simulating accurately strong 3-D shock wave/turbulent boundary layer interactions (SBLIs) and high-alpha flows with classical turbulence models are investigated.

These flows are characterized by the appearance of strong crossflow separation. In view of recent additional evidence, a previously published flow analysis, which attributes the poor performance of Cited by: 7. Flowfield analysis for successive oblique shock wave-turbulent boundary layer interactions / (Washington: National Aeronautics and Space Administration, Ames Research Center ;, ), by Chen-Chih Sun, Morris E.

Childs, and Washington State University. Dept. of. The two-dimensional 24° compression corner and the three-dimensional asymmetric 7° × 11° double fin configuration are simulated as examples of shock wave/turbulent-boundary-layer interactions.

Incoming Mach numbers were chosen and for the 2D case and for the 3D interaction. In order to overcome the cost associated with the low-Re turbulence models, a more advanced wall function approach has been implemented within OpenFoam, and tested together with a standard log-law based wall function in the prediction of flows which involve 2-D shock wave/turbulent boundary layer interactions (SWTBLIs).Author: Xinguang Wang, Timothy Craft, Hector Iacovides.

Shang, J. S Hankey, W. L Law, C. H Numerical simulation of shock wave/turbulent boundary-layer interaction AIAA J 14 Chapman, D. R Kuhen, D. M Larson, H. K Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition NACA TN An efficient application of this technique however requires reliable design tools.

The calculation of the compressor flow makes high demands on the flow solver and the applied turbulence model. Particularly the additional losses at transonic flow conditions caused by shock waves and shock/boundary layer interactions have to be taken into : L.

Hilgenfeld, L. Fottner. Second, the shock wave/turbulent boundary layer interactions induced by inserting axisymmetric wedges (wedge angles 4" and 10") in a Mach 6 free stream were studied.

Alzner and Zakkay (ref. 3) and Zakkay (ref. 4) performed experiments in these flow fields. They measured the surface heat transfer rates, static pressures, and pi tot. - Shock Wave Boundary-Layer Interactions Edited by Holger Babinsky and John K.

Harvey Frontmatter More informatio n SHOCK WAVE–BOUNDARY-LAYER INTERACTIONS Shock wave–boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft.

Turbulence modeling both addresses a fundamental problem in physics, 'the last great unsolved problem of classical physics,' and has far-reaching importance in the solution of difficult practical problems from aeronautical engineering to dynamic meteorology.

However, the growth of supercom­ puter. Shop our online store from wide selection of Shock Wave Boundary Layer with discounted prices for sale. Browse Shock Wave Boundary Layer sales available today from Ebay.

Gucci Black Nylon w Leather Trim Rolling Wheeled Duffle Bag Luggage Travel 24" Gucci Black Nylon - $   The purpose of this paper is to develop a second-moment closure with a near-wall turbulent pressure diffusion model for three-dimensional complex flows, and to evaluate the influence of the turbulent diffusion term on the prediction of detached and secondary by:.

Knight, D., "Numerical Simulation of 3-D Shock Wave Turbulent Boundary Layer Interactions", AGARD/VKI Special Course on Shock-Wave Boundary-Layer Interactions in Supersonic and Hypersonic Flows, AGARD R, Maypp. to The Book Review Index, pagelists the books reviewed duringthe author, publisher, and reviewer, and the volume, issue number, and page on which the review appeared.

Algebraic Turbulence Modeling for Swept Shock-Wave/Turbulent Boundary-Layer Interactions J New Methodology for the Measurement of Surface.Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gasdynamics and frequently a defining feature in high speed aerodynamic flowfields.

The interactions can be found in practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines.