Direct Numerical Simulation of Transition and Turbulence in a Spatially Evolving Boundary Layer

Mohan, Man; Moin, Parviz

doi:10.1006/jcph.1993.1210

Cited by 223 publications

(82 citation statements)

References 7 publications

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“…It seems not to depend significantly on which wall approach is used. This defect has been reported in previous studies and is a common feature of simulations using finite-difference methods on relatively coarse meshes (see Rai & Moin, 1993). For the present purposes, the differences were considered acceptably small and it was thus concluded that the upstream turbulence is a satisfactory representation of the wind tunnel boundary layer, virtually independent of which of the three surface conditions are used.…”

Section: E-04supporting

confidence: 53%

Flow around a cube in a turbulent boundary layer: LES and experiment

Lim

Thomas

Castro

2009

Journal of Wind Engineering and Industrial Aerodynamics

136

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We present a numerical simulation of flow around a surface mounted cube placed in a turbulent boundary layer which, although representing a typical wind environment, has been specifically tailored to match a series of wind tunnel observations. The simulations were carried out at a Reynolds number, based on the velocity U at the cube height h, of 20, 000 -large enough that many aspects of the flow are effectively Reynolds number independent. The turbulence intensity was about 18% at the cube height, and the integral length scale L u x was about 0.8 times the cube height h. The Jenson number Je = h/z0, based on the approach flow roughness length z0, was 600, to match the wind tunnel situation. The computational mesh was uniform with a spacing of h/32, aiding rapid convergence of the multigrid solver, and the governing equations were discretised using second order finite differences within a parallel multiblock environment. The results presented include detailed comparison between measurements and LES computations of both the inflow boundary layer and the flow field around the cube including mean and fluctuating surface pressures. It is concluded that provided properly formulated inflow and surface boundary conditions are used, LES is now a viable tool for use in wind engineering problems concerning flow over isolated bodies. In particular, both mean and fluctuating surface pressures can be obtained with a similar degree of uncertainty as usually associated with wind tunnel modelling.

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Section: E-04supporting

confidence: 53%

Flow around a cube in a turbulent boundary layer: LES and experiment

Lim

Thomas

Castro

2009

Journal of Wind Engineering and Industrial Aerodynamics

136

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“…Such a spatial increment is approximately of the order of the displacement boundary layer thickness, in boundary layer scale Ax+ ~ 40. Although this valué is slightly smaller than that used by Rai and Moin [15] for the case M = 0.0849 (Ax+ ~ 25), it involves the use of larger number of points per wavelength than those used by Fasel and Konzelmann [7], in their computations of the incompressible case with a spatial fourth order scheme.…”

Section: Appendix a Preliminary Tests And Convergence Analysismentioning

confidence: 83%

“…9 for local Reynolds numbers VRex = 704 and 652 and a¡ ~ 2.6 and 2.1, which correspond to M = 0.3 and M = 0.7, respectively. In order to minimize the a¡ variations, the computational domain is restricted to x e [10,15]; the associated non-dimensional wavelengths are also essentially constant, with a small variation around respectively 0.27 and 0.3 (see Fig. 10).…”

Section: 9mentioning

confidence: 99%

Unsteady residual distribution schemes for transition prediction

Meseguer

Valero

Martel

et al. 2010

Aerospace Science and Technology

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ARTICLE INFO ABSTRACTIn this work, the unsteady simulation of the Navier-Stokes equations is carried out by using a Residual Distribution Schemes (RDS) methodology. This algorithm has a compact stencil (cell-based computations) and uses a finite element like method to compute the residual over the cell. The RDS method has been successfully proven in steady Navier-Stokes computation but its application to fully unsteady configurations is still not closed, because some of the properties of the steady counterpart can be lost. Kevwords-Here, we proposed a numerical solution for unsteady problems that is fully compatible with the original Unsteady numerical simulation approach. In order to check the method, we chose a very demanding test case, namely the numerical Finite element methods simulation of a Tollmien-Schlichting (TS) wave in a 2D boundary layer. The evolution of this numerical Boundary layer transition perturbation is accurately computed and checked against theoretical results.

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“…Some previous investigations ͑e.g., Rai and Moin, 35 Pirozzoli et al, 36 Teramoto 18 ͒ suggested that at low Mach number ͑M 1 = 2.0͒ the shock-wave/boundary-layer interaction will undergo an oblique breakdown and finally transition to turbulence. As this study confirms that the two high Mach numbers M 1 = 4.5 and M 1 = 6.85 have very similar linear growth rate, the final breakdown process is likely to be similar.…”

Section: Early Stage Of Nonlinear Breakdown To Turbulencementioning

confidence: 99%

The effect of Mach number on unstable disturbances in shock/boundary-layer interactions

et al. 2007

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The effect of Mach number on the growth of unstable disturbances in a boundary layer undergoing a strong interaction with an impinging oblique shock wave is studied by direct numerical simulation and linear stability theory ͑LST͒. To reduce the number of independent parameters, test cases are arranged so that both the interaction location Reynolds number ͑based on the distance from the plate leading edge to the shock impingement location for a corresponding inviscid flow͒ and the separation bubble length Reynolds number are held fixed. Small-amplitude disturbances are introduced via both white-noise and harmonic forcing and, after verification that the disturbances are convective in nature, linear growth rates are extracted from the simulations for comparison with parallel flow LST and solutions of the parabolized stability equations ͑PSE͒. At Mach 2.0, the oblique modes are dominant and consistent results are obtained from simulation and theory. At Mach 4.5 and Mach 6.85, the linear Navier-Stokes results show large reductions in disturbance energy at the point where the shock impinges on the top of the separated shear layer. The most unstable second mode has only weak growth over the bubble region, which instead shows significant growth of streamwise structures. The two higher Mach number cases are not well predicted by parallel flow LST, which gives frequencies and spanwise wavenumbers that are significantly different from the simulations. The PSE approach leads to good qualitative predictions of the dominant frequency and wavenumber at Mach 2.0 and 4.5, but suffers from reduced accuracy in the region immediately after the shock impingement. Three-dimensional Navier-Stokes simulations are used to demonstrate that at finite amplitudes the flow structures undergo a nonlinear breakdown to turbulence. This breakdown is enhanced when the oblique-mode disturbances are supplemented with unstable Mack modes.

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Direct Numerical Simulation of Transition and Turbulence in a Spatially Evolving Boundary Layer

Cited by 223 publications

References 7 publications

Flow around a cube in a turbulent boundary layer: LES and experiment

Flow around a cube in a turbulent boundary layer: LES and experiment

Unsteady residual distribution schemes for transition prediction

The effect of Mach number on unstable disturbances in shock/boundary-layer interactions

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