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Saturday, August 1, 2020 | History

3 edition of On the freestream matching condition for stagnation point turbulent flows found in the catalog.

On the freestream matching condition for stagnation point turbulent flows

On the freestream matching condition for stagnation point turbulent flows

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Published by Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, National Technical Information Service, distributor in Hampton, VA, [Springfield, Va .
Written in English

    Subjects:
  • Free flow.,
  • Plane strain.,
  • Stagnation point.,
  • Turbulent flow.

  • Edition Notes

    StatementCharles G. Speziale.
    SeriesICASE report -- no. 89-2., NASA contractor report -- 181765., NASA contractor report -- NASA CR-181765.
    ContributionsInstitute for Computer Applications in Science and Engineering.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15407381M

    Results for free turbulent shear flows and wall-bounded turbulent shear flows, from a vorticity transport perspective, are presented. The flux of vorticity across a channel is constant. Near one wall the transfer from viscous stress to Reynolds stress is inextricably linked to the transport of vorticity and the dominant turbulent vorticity. Methods and related apparatus embodiments are disclosed that allow novel Conformal Vortex Generator and/or Elastomeric Vortex Generator art to improve energy efficiency and control capabilities at many surface points of a body or object moving at speed in aero/hydrodynamic Newtonian fluids, by reducing; shock energy losses, surface flow turbulence, and/or Cited by:

      CARS is a well-known optical four-wave mixing diagnostic technique which has been used extensively in combustion, gas discharges, and aerospace applications for measurements of rotational/translation temperature and, to a lesser extent, of the vibrational distribution function [].Recently, its use has become more prevalent in studies of Cited by: Full text of "Minnowbrook II Workshop on Boundary Layer Transition in Turbomachines" See other formats.

    AA Aeroacoustics - Advanced Measurement and Experiment • Wednesday, 11 January • hrs. A shear-wake flow forms in the post-separation region downstream of a splitter plate dividing two boundary layer flows that have different freestream velocities. Thus, the upstream (in-flow) condition for the shear-wake is a wall-bounded flow, while the downstream (out-flow) state is a two-stream shear layer.


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On the freestream matching condition for stagnation point turbulent flows Download PDF EPUB FB2

The problem of plane stagnation point flow with freestream turbulence is examined from a basic theoretical standpoint. It is argued that the singularity which arises in the standard K–ε model results from the use of an inconsistent freestream boundary by: 9.

Get this from a library. On the freestream matching condition for stagnation point turbulent flows. [C G Speziale; Institute for Computer Applications in Science and Engineering.]. A schematic representation of fluid motion in a stagnation-point flow is shown in Figure a.A description of the impinging jet system for creating the axisymmetrical flow is presented in Figure this system, a fluid stream impinges on a flat surface at a right angle to it and flows away radially in all directions.

Abid, R. and Speziale, C.G. () The freestream matching condition for stagnation point turbulent flows: An alternative formulation, ASME J. Appl. Mech. 63, pp. 95– ADS zbMATH CrossRef Google ScholarCited by: 4. Charles G. Speziale's research works w citations and 8, reads, including: Computing non-equilibrium turbulent flows with time-dependent RANS and VLES.

The Freestream Matching Condition for Stagnation Point Turbulent Flows: An Alternative Formulation.

R Turbulence, Energy dissipation, Equilibrium (Physics), Plane strain, Boundary-value problems, Stagnation flow, Vortices. Dynamic Stability of a Rotor Filled or Partially Filled With Liquid Book Proposal Guidelines; Resources. A stagnation point flow of the form U = (0, A y, - A z) is unstable to three-dimensional disturbances.

It has been shown that the vorticity components of such a disurbance that are perpendicular. Hsue-shen Tsien, in Collected Works of H.S. Tsien (–), Hypersonic flows are flow fields where the fluid velocity is much larger than the velocity of propagation of small disturbances, the velocity of sound.

von Kármán [1] has pointed out that in many ways the dynamics of hypersonic flows is similar to Newton's corpuscular theory of aerodynamics. The role of high performance computing in current research on transitional and turbulent flows is undoubtedly very important.

This review volume provides a good platform for leading experts and researchers in various fields of fluid mechanics dealing with transitional and turbulent flows to synergistically exchange ideas and present the state.

Review And Assessment Of Turbulence Transition Models 38 where PL is the production of laminar kinetic energy by large-scale turbulent fluctuations, and DL is the near- wall dissipation of the laminar kinetic energy, which are described as: In the Walters-Leylek model, the turbulent dissipation rate equation is modified as where Cε2 is a.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA In physics and fluid mechanics, a boundary layer is the layer of fluid in the immediate vicinity of a bounding surface where the effects of viscosity are significant. In the Earth's atmosphere, the atmospheric boundary layer is the air layer near the ground affected by diurnal heat, moisture or momentum transfer to or from the surface.

On an aircraft wing the boundary layer is the part of. A novel two-way coupled Eulerian–Eulerian CFD formulation was developed to simulate drifting snow based on turbulent drag and a new viscous treatment of the drifting snow phase, “Stagnation point flows with freestream turbulence – the matching condition,” AIAAJ, vol.

23, pp. –, Author: Ziad Boutanios, Hrvoje Jasak. Past the stagnation point, the jet is deflected in the direction of the counterflow. The jet core entrains part of this deflected flow, creating vortices.

The distance from the jet exit to the stagnation point is referred to as the penetration length x p. Additionally, the iso-contour of zero axial velocity forms the stagnation surface, while Author: Marc Rovira.

@article{osti_, title = {Numerical solutions of turbulent models for flow over a flat plate with angle of attack}, author = {Truncellito, N.T.

and Yeh, H. and Lior, N.}, abstractNote = {Numerical solutions of the two-dimensional boundary layer equations were developed as applied to flow over a flat plate at various angles of attack.

The turbulent integral length scale for the same turbulence grid configuration as in MUR was experimentally measured to be around mm. Regarding the stagnation region, the effect of the turbulence intensity was to increase the heat transfer by 9%, which then converge to similar heat transfer levels as MUR in the laminar : Tânia S.

Cação Ferreira, Tony Arts, Emma Croner. Full text of "Engineering Calculation Methods For Turbulent Flow" See other formats. Unfortunately, this book can't be printed from the OpenBook. If you need to print pages from this book, we recommend downloading it as a PDF.

Visit to get more information about this book, to buy it in print, or to download it as a free PDF. Propulsion 2 notes 1. Unit-1 AIRCRAFT GAS TURBINES Impulse and reaction blading of gas turbines – Velocity triangles and power output – Elementary theory – Vortex theory – Choice of blade profile, pitch and chord – Estimation of stage performance – Limiting factors in gas turbine design- Overall turbine performance – Methods.

transition location; tangency point for a sphere/cone, Fig. ; stagnation-point value; for a turbulent boundary layer t,ref reference stagnation-point value t2 conditions at the stagnation point downstream of a normal shock wave conditions at the wall (or surface); conditions at the surface of a wedge, based on inviscid flow tv vat.

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web; books; video; audio; software; images; Toggle navigation.The effect of thermal and chemical boundary conditions on the structure and chemical composition of the wake behind a 3D Mach 7 sphere-cone at an angle of attack of 5 degrees and an altitude of roug m is explored.

A special emphasis is placed on determining the number density of chemical species which might lead to detection via the electromagnetic Cited by: 1.