DNS 1-5 Description: Difference between revisions
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Although for DNS the inflow boundary conditions are different than RANS, they must guarantee the same boundary layer properties at a given point upstream of the rounded step, i.e., <math>{x/H = -3.51}</math>, to allow a valid comparison. | Although for DNS the inflow boundary conditions are different than RANS, they must guarantee the same boundary layer properties at a given point upstream of the rounded step, i.e., <math>{x/H = -3.51}</math>, to allow a valid comparison. | ||
At the reference position <math>{x_{ref}}</math>, the properties to be matched are the Reynolds number based on the momentum thickness <math>{Re_{\theta} = ????}</math> and the Reynolds number based on the friction velocity <math>{Re_{\tau} = ???}</math>. | At the reference position <math>{x_{ref}}</math>, the properties to be matched are the Reynolds number based on the momentum thickness <math>{Re_{\theta} = ????}</math> and the Reynolds number based on the friction velocity <math>{Re_{\tau} = ???}</math>. | ||
As a technique to promote the laminar-turbulent transition and reduce the upstream length of the domain, inspired by the work of [ | As a technique to promote the laminar-turbulent transition and reduce the upstream length of the domain, inspired by the work of [[Lib:UFR_3-36_References#5|Housseini et al.]]] and [‌[Lib:DNS_1-5_description#6|Schlatter and Örlü]], a local tripping term was used. | ||
To define the mesh density and the computational domain size that ensure the target boundary layer integral parameters at the reference location <math>{x_{ref}}</math>, a precursory computational campaign for the turbulent flow over a flat plate was performed. | To define the mesh density and the computational domain size that ensure the target boundary layer integral parameters at the reference location <math>{x_{ref}}</math>, a precursory computational campaign for the turbulent flow over a flat plate was performed. | ||
According to the outcomes of this campaign, the inlet boundary is located at <math>{x/H = -12.71}</math>, where the Blasius laminar velocity profile computed at <math>{Re_x=650,000}</math>, the uniform static pressure and the uniform total temperature (see [[Lib:UFR_3-36_Test_Case#table2|UFR 3-36: Table 2]]) are imposed. At location <math>{x/H = -12.1}</math>, within the laminar boundary layer region, the tripping source term is activated to promote the transition to turbulence. This set-up corresponds to the laminar and turbulent distances <math>{L_{l} = ???}</math> and <math>{L_{t} = ???}</math>, respectively, see [[Lib:DNS_1-5_description&action#figure2|Fig. 2]]. | According to the outcomes of this campaign, the inlet boundary is located at <math>{x/H = -12.71}</math>, where the Blasius laminar velocity profile computed at <math>{Re_x=650,000}</math>, the uniform static pressure and the uniform total temperature (see [[Lib:UFR_3-36_Test_Case#table2|UFR 3-36: Table 2]]) are imposed. At location <math>{x/H = -12.1}</math>, within the laminar boundary layer region, the tripping source term is activated to promote the transition to turbulence. This set-up corresponds to the laminar and turbulent distances <math>{L_{l} = ???}</math> and <math>{L_{t} = ???}</math>, respectively, see [[Lib:DNS_1-5_description&action#figure2|Fig. 2]]. | ||
Revision as of 21:20, 30 January 2023
Introduction
The HiFi-TURB-DLR rounded step test case is a case in which a turbulent boundary layer flows over a flat plate before reaching a planar rounded backward step. The particular geometry generates an adverse pressure gradient which accelerates the boundary layer upstream the step before inducing an incipient separation above the smooth step, a flow physics that is well known to be not correctly predicted by state-of-the-art Reynolds-Averaged Navier-Stokes (RANS) models.
Review of previous studies
The design of the test case was inspired by the experimental work on the flow around an axisymmetric test body of Disotell et al. and Disotell et al. (2017). Disotell et al. focused their study of the possible separation and reattachment in the rear part of the body. The original test case is here revised as a 2D planar flow problem without any tunnel walls but with a far-field condition opposite to the solid wall. The reasons for using a planar geometry are thoroughly discussed in UFR 3-36 Test Case.
Description of the test case
Geometry and flow parameters
The test case is designed as a numerical experiment with the aim of comparing RANS results to DNS data. The flow problem was defined by DLR with the aid of RANS calculations to get a condition with incipient separation. Other cases with moderate and full separation were also designed by DLR, see Alaya et al., but for the present uDNS only the incipient condition for the Reynolds number was considered, where is the step height. The geometry of the curved step is shown in Fig. 2 and its definition is reported in UFR 3-36 Test Case.
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| Figure 2: Set-up for DNS Simulation |
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The simulation was performed by using the UNIBG in-house software MIGALE, see Bassi et al. (2015), on a computational mesh made of hexahedral elements with quadratic edges, a wall-normal growth ratio of and a first cell height of , cf. DNS 1-5 Computational Details. The average time step size was CTU, where the convective time unit (CTU) is defined as the ratio between and the freestream velocity . The turbulence statistics were collected for CTU.
Computation domain and boundary conditions
Although for DNS the inflow boundary conditions are different than RANS, they must guarantee the same boundary layer properties at a given point upstream of the rounded step, i.e., , to allow a valid comparison. At the reference position , the properties to be matched are the Reynolds number based on the momentum thickness and the Reynolds number based on the friction velocity . As a technique to promote the laminar-turbulent transition and reduce the upstream length of the domain, inspired by the work of Housseini et al.] and [[Lib:DNS_1-5_description#6|Schlatter and Örlü]], a local tripping term was used. To define the mesh density and the computational domain size that ensure the target boundary layer integral parameters at the reference location , a precursory computational campaign for the turbulent flow over a flat plate was performed. According to the outcomes of this campaign, the inlet boundary is located at , where the Blasius laminar velocity profile computed at , the uniform static pressure and the uniform total temperature (see UFR 3-36: Table 2) are imposed. At location , within the laminar boundary layer region, the tripping source term is activated to promote the transition to turbulence. This set-up corresponds to the laminar and turbulent distances and , respectively, see Fig. 2. At the outlet boundary, placed at , the static pressure is imposed, see UFR 3-36: Table 2. To mitigate spurious perturbations possibly originating at the outlet boundary, the mesh is coarsened in the streamwise direction for . The upper boundary is a permeable far-field Riemann boundary condition located from the no-slip adiabatic wall and computed via the exact Riemann solver. Finally, side planes are considered as periodic with a distance from each other of .
References
- Disotell, K. J. and Rumsey, C. L.: Modern CFD validation of turbulent flow separation on axisymmetric afterbodies.
- Disotell, K. J. and Rumsey, C. L. (2017): Development of an axisymmetric afterbody test case for turbulent flow separation validation. NASA/TM-2017219680, Langley Research Center, Hampton, Virginia
- Alaya, E., Grabe, C. and Knopp, T. (2021): Design of a parametrized numerical experiment for a 2D turbulent boundary layer flow with varying adverse pressure gradient and separation behaviour. DLR-IB-AS-GO-2020-109, DLR-Interner Bericht, DLR Institute of Aerodynamics and Flow Technology
- Bassi, F., Botti, L., Colombo, A. C, Ghidoni, A. and Massa, F. (2016): On the development of an implicit high-order Discontinuous Galerkin method for DNS and implicit LES of turbulent flows. European Journal of Mechanics, B/Fluids, Vol. 55(2), pp. 367-379
- S. Hosseini, R. Vinuesa, P. Schlatter, A. Hanifia and D. Henningson Direct numerical simulation of the flow around a wing section at moderate Reynolds number, International Journal of Heat and Fluid Flow, 61:117–128, 2016
- Schlatter, P. and Örlü, R. Turbulent boundary layers at moderate Reynolds numbers: inflow length and tripping effects,Journal of Fluid Mechanics, 710:5–34, 2012
Contributed by: Francesco Bassi, Alessandro Colombo, Francesco Carlo Massa — Università degli studi di Bergamo (UniBG)
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