Comparison of Multiequation Turbulence Models for Several Shock Boundary-Layer Interaction Flows

Viegas, J. R.; Horstman, C. C.

doi:10.2514/3.61232

Cited by 70 publications

(10 citation statements)

References 13 publications

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“…The agreement might, however, be considered fair from the standpoint of accuracy requirements for much engineering work, and in view of the strong adverse pressure-gradient. Results very similar to this were reported by Viegas and Horstman [20], and the failure of the computation to more accurately simulate the flow field lies with the turbulence model. Reasons for the lack of accuracy are well-known and understood in the field of turbulence-modeling research and development; for example, see Reference 24.…”

Section: Straight Circular Ductsupporting

confidence: 77%

“…The experimental results seem inconclusive in this regard, with the original study indicating that there was separation [ 191, but later work suggesting that separation probably did not occur [20].…”

Section: Straight Circular Ductmentioning

confidence: 65%

“…The two sets of experimental wall pressure data correspond to two different measurement approaches; one with the shock wave at a single location [20] in the test section (diamonds), and the other with the shock wave relocated to various positions [21] relative to the probe-survey location (circles). The case with a single shock position is, in principle, most like the computation, but for that case the exact inlet flow profile is not known (and therefore not used for the computation).…”

Section: Straight Circular Ductmentioning

confidence: 99%

“…where The Riemann invariant based on meridional velocity is given by where v,= 7 u + w (22) The flow variables on the right-hand-side of Equation (20) are taken from the interior, and all derivatives are obtained by first-order (backward) differences from boundary to interior. The resulting formulation is solved for R-at the inlet boundary.…”

Section: Boundary Conditionsmentioning

confidence: 99%

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Rapid numerical simulation of viscous axisymmetric flow fields

Tweedt

Chima

1996

34th Aerospace Sciences Meeting and Exhibit

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A two-dimensional Navier-Stokes code has been developed for rapid numerical simulation of axisymmebic flow fields, including flow fields with an azimuthal velocity component. The azimuthal-invariant Navier-Stokes equations in a cylindrical coordinate system are mapped to a general body-fitted coordinate system, with the streamwise viscous terms then neglected by applying the thinlayer approximation. Turbulence effects are modeled using an algebraic model, typically the Baldwin-Lomax turbulence model, although a modified Cebeci-Smith model can also be used. The equations are discretized using central finite differences and solved using a multistage Runge-Kutta algorithm with a spatially-varying time step and implicit residual smoothing.Results are presented for calculations of supersonic flow over a waisted body-of-revolution, transonic flow through a normal shock wave in a straight circular duct of constant cross-sectional area, swirling supersonic (inviscid) flow through a strong shock in a straight radial duct, and swirling subsonic flow in an annular-to-circular diffuser duct. Comparisons between computed and experimental results a r e in fair to good agreement, demonstrating that the viscous code can be a useful tool for practical engineering design and analysis work.

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Section: Straight Circular Ductsupporting

confidence: 77%

Section: Straight Circular Ductmentioning

confidence: 65%

Section: Straight Circular Ductmentioning

confidence: 99%

Section: Boundary Conditionsmentioning

confidence: 99%

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Rapid numerical simulation of viscous axisymmetric flow fields

Tweedt

Chima

1996

34th Aerospace Sciences Meeting and Exhibit

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“…The location of the pressure rise is underpredicted by the code. Previous results obtained with zero and one equation turbulence models have shown the same tendency [11,20,22].…”

Section: Experiments Of Settles [19)supporting

confidence: 76%

A Fully—Implicit 2‐D Navier-Stokes Algorithm for Unstructured Grids

Kergaravat

Jacon

Okong’o

et al. 1998

International Journal of Computational Fluid Dynamics

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A fully-implicit algorithm is developed for the two-dimensional, compressible, Favreaveraged Navier-Stokes equations. It incorporates the standard k -E turbulence model of Launder and Spalding and the low Reynolds number correction of Chien. The equations are solved using an unstructured grid of triangles with the flow variables stored at the centroids of the cells. A generalization of wall functions including pressure gradient effects is implemented to solve the near-wall region for turbulent flows using a separate algorithm and a hybrid grid. The inviscid fluxes are obtained from Roe's flux difference split method. Linear reconstruction of the flow variables to the cell faces provides second-order spatial accuracy. Turbulent and viscous stresses as well as heat transfer are obtained from a discrete representation of Gauss's theorem. Interpolation of the flow variables to the nodes is achieved using a second-order accurate method. Temporal discretization employs Euler, Trapezoidal or 3-Point Backward differencing. An incomplete LV factorization of the Jacobian matrix is implemented as a preconditioning method. The accuracy of the code and the efficiency of the solution strategy are presented for three test cases: a supersonic turbulent mixing layer, a supersonic laminar compression corner and a supersonic turbulent compression corner.

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Introduction of turbulent model in a mixed finite volume/finite element method

Ribault

Buffat

Jeandel

1995

Numerical Methods in Fluids

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SUMMARYThe aim of this work is to present a new numerical method to compute turbulent flows in complex configurations. With this in view, a k-E model with wall functions has been introduced in a mixed finite volumehinite element method. The numerical method has been developed to deal with compressible flows but is also able to compute nearly incompressible flows. The physical model and the numerical method are first described, then validation results for an incompressible flow over a backward-facing step and for a supersonic flow over a compression ramp are presented. Comparisons are performed with experimental data and with other numerical results. These simulations show the ability of the present method to predict turbulent flows, and this method will be applied to simulate complex industrial flows (flow inside the combustion chamber of gas turbine engines). The main goal of this paper is not to test turbulence models, but to show that this numerical method is a solid base to introduce more sophisticated turbulence model.

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Comparison of Multiequation Turbulence Models for Several Shock Boundary-Layer Interaction Flows

Cited by 70 publications

References 13 publications

Rapid numerical simulation of viscous axisymmetric flow fields

Rapid numerical simulation of viscous axisymmetric flow fields

A Fully—Implicit 2‐D Navier-Stokes Algorithm for Unstructured Grids

Introduction of turbulent model in a mixed finite volume/finite element method

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