3 edition of **Supersonic boundary-layer flow turbulence modeling** found in the catalog.

Supersonic boundary-layer flow turbulence modeling

- 238 Want to read
- 36 Currently reading

Published
**1993**
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC, Springfield, Va
.

Written in English

- Turbulence.,
- Heat -- Transmission.

**Edition Notes**

Other titles | Supersonic boundary layer flow turbulence modeling. |

Statement | Chi-Rong Wang. |

Series | NASA technical memorandum -- 105893. |

Contributions | United States. National Aeronautics and Space Administration. |

The Physical Object | |
---|---|

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL15368413M |

In this study, the ability of standard one- or two-equation turbulence models to predict mean and turbulence profiles, the Reynolds stress, and the turbulent heat flux in hypersonic cold-wall boundary-layer applications is investigated. The turbulence models under investigation include the one-equation model of Spalart–Allmaras, the baseline k - ω model by Menter, as well as the shear Author: Junji Huang, Jorge-Valentino Bretzke, Lian Duan. Compressible flow (or gas dynamics) is the branch of fluid mechanics that deals with flows having significant changes in fluid all flows are compressible, flows are usually treated as being incompressible when the Mach number (the ratio of the speed of the flow to the speed of sound) is less than (since the density change due to velocity is about 5% in that case).

turbulence modeling, NASA has established the Turbulence Modeling Resource (TMR) website and has issued the NASA 40% Challenge. The aim of this challenge is to identify and improve/develop turbulence and transition models as well as numerical techniques to achieve aAuthor: Francis K Acquaye. This paper presents our recent work on investigating velocity slip boundary conditions’ effects on supersonic flat plate boundary layer flow stability. The velocity-slip boundary conditions are adopted and the flow properties are obtained by solving boundary layer equations. Stability analysis of two such boundary layer flows is performed by using the Linear stability : Xin He, Kai Zhang, Chunpei Cai.

The paper is devoted to an experimental study of laminar-turbulent transition in a three-dimensional supersonic boundary layer. The experiments were conducted at the low nose supersonic wind tunnel T of ITAM at Mach numbers M=2 - 4. Model is a symmetrical wing with a 45° sweep angle, a 3 percent-thick circular-arc by: 2. Compressible Turbulent Boundary Layer Simulations: Resolution E ects and Turbulence Modeling Jonathan Poggie Air Force Research Laboratory, Wright-Patterson AFB, Ohio USA Direct numerical simulation (DNS) and high- delity, implicit large-eddy simulation (HFILES) were carried out for turbulent boundary layers at Mach and Transi-.

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Get this from a library. Supersonic boundary-layer flow turbulence modeling. [Chi-Rong Wang; United States. National Aeronautics and Space Administration.].

Within the boundary layer, the flow is supersonic in the outer layer and subsonic near the wall, although the sonic line is located very close to the wall at high Mach number. A temperature gradient develops across the boundary layer due to the conversion of kinetic energy to heat as the flow velocity decreases.

A spatially developing supersonic adiabatic flat plate boundary layer flow (at M∞ = and Reθ ≈ ) is analyzed by means of direct numerical simulation.

Development of an Intermittency Equation for the Modeling of the Supersonic/Hypersonic Boundary Layer Flow Transition Article (PDF Available) in Flow Turbulence and Combustion 87(1) Shock Boundary-Layer Interactions.\/span>\"@ en\/a> ; \u00A0\u00A0\u00A0\n schema:description\/a> \" Using the most recent data, Turbulent Shear Layers in Supersonic Flow describes the physical mechanisms Supersonic boundary-layer flow turbulence modeling book turbulent supersonic flows, emphasizing the similarities and differences between compressible and incompressible flows.

(1). I can only guess that you are talking about the supersonic nozzle with the exit Me=2,4,6,8. (2). With the nozzle contour properly designed,that is, shock free condition, the pressure on the boundary layer will be smooth and continuous from the nozzle throat to the nozzle exit.

The engineering computation of turbulent flows is mainly based on turbulence modeling, however, accurate aerothermal computation of hypersonic turbulent Cited by: However, boundary layer theory [4] indicates that the use of Reynolds analogy requires a wide range of turbulent Prandtl numbers in order to properly model the turbulent thermal fluxes in pipe flow and a heated boundary layer flow.

Closer to the present work, a recent experiment [5] of a supersonic compression ramp flow also revealed that the File Size: KB. 2 Boundary-Layer Equations Continuity Momentum Energy and the Strong Reynolds Analogy 3 Subsonic Flows Mean flow behavior The viscous sublayer The law-of-the-wall and the defect-law The law-of-the-wake An alternative outer-flow scaling The data Discussion of Reynolds-number effects.

Fig. illustrates the important stages of development of a turbulent boundary layer over a smooth flat surface, depicting the gradual expansion of the outer interface between the undisturbed outer flow and the turbulent layer as flow moves downstream of some origin, presumed in this discussion to be at y 1 =0.

The interface between the wall. Computer Methods in Applied Mechanics and Engineering 89 () North-Holland Performance of turbulence models to predict supersonic boundary layer flows F.

Hanine and A. Kourta' Institut de Manique des fluides de Toulouse, CNRS U. D, Avenue du professeur Camille Soula, Toulouse Cedex, France Received 20 September Revised manuscript received 7 February Cited by: 2. 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. The subject paper briefly reviews the studies of a wide class of two- and three-dimensional shock-wave boundary-layer interactions.

Some principal physical processes are singled out on the basis of mean flow and turbulence measurements. The efforts to make more precise some flows peculiarities under 3-D interactions conditions are by: 8. The majority of the turbulence modeling works that have been done in the last thirty years, correspond to k-ε models.

Launder [10] introduced the model in its present form. The k-ε model overestimates the skin friction coefficient when applied to the boundary layer flows. Hi, Supersonic flow and subsonic flow as of cfd is concern depends upon the boundary conditions.

Like if we see the characteristics of the flow in subsonic flow one will come out of the domain and two will go inside domain at the outlet two will go out and one will come in so accordingly we need to give information at the boundary as two variables have to specified for subsonic flow at inlet.

3 Equations for turbulent flow 4 Fundamental concepts 5 Morkovin’s hypothesis 6 Mixing layers 7 Boundary layer mean-flow behavior 8 Boundary layer turbulence behavior 9 Perturbed boundary layers 10 Shock boundary layer interactions Download Turbulent Shear Layers in Supersonic Flow, 2nd Edition.

This book has been developed from the author’s lecture notes used in presenting a post-graduate course on turbulence modeling at the University of Southern University. The primary goal of this book is to provide a Systematic approach to developing a set of constitutive equations suitable for computation of turbulence flows.5/5(8).

Using the most recent data, Turbulent Shear Layers in Supersonic Flow describes the physical mechanisms of turbulent supersonic flows, emphasizing the similarities and differences between compressible and incompressible flows.

The book begins with a basic overview of the field, essential equations, and core concepts of compressible turbulence.3/5(2). Direct Numerical Simulation of Pressure Fluctuations Induced by Supersonic Turbulent - turbulence modeling (pressure-strain terms in the transport Acoustic radiation due to supersonic turbulent boundary layer medium for the left-hand side.

Phillips () extended Lighthill’s ideas to treat the. Abstract. A new transition/turbulence model considering the modes of instability and the compressibility effects is established. Based on the Menter’s SST model, it adds the contribution of nonturbulent fluctuations into the effective : S.

Fu, L. Wang. The aerodynamic boundary layer was first defined by Ludwig Prandtl in a paper presented on Aug at the third International Congress of Mathematicians in Heidelberg, simplifies the equations of fluid flow by dividing the flow field into two areas: one inside the boundary layer, dominated by viscosity and creating the majority of drag experienced by the boundary body; and.Basics of Y Plus, Boundary Layer and Wall Function in Turbulent Flows Before getting into the details of the turbulent models let us discuss an important concept known as and know how it is related to turbulence modeling, mesh generation process and how it is going to affect the CFD end result.The goal of this thesis is to compare the performance of several eddy-viscosity turbulence models for computing supersonic nozzle exhaust flows.

These flows are of relevance in the development of future supersonic transport airplane. Flow simulations of exhaust flows from three supersonic nozzles are computed using ANSYS Fluent. Simulation results are compared to experimental data to assess Cited by: 3.