Automatic Transition Prediction for High-Lift Systems Using a Hybrid Flow Solver

Krumbein, Andreas

doi:10.2514/1.16173

Cited by 12 publications

(4 citation statements)

References 15 publications

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“…Thus, as shown in [6], the large number of grid points near the wall for a high resolution of the boundary layers, the adaptation of the NavierStokes grid in the laminar, turbulent, and transitional boundary-layer regions and the generation of new adapted grids for the RANS solver after every step of the transition location iteration are avoided, and the computational time can be massively reduced. In addition, the number of RANS iteration cycles between two steps of the transition location iteration can be highly reduced compared to an approach where the boundary-layer parameters are computed directly from the RANS grid [23,24], because the surface pressure converges significantly faster in the RANS computation than the boundarylayer velocity profiles [25], which are the basis for the computation of the boundary-layer parameters.…”

Section: Transition Prediction Coupling Structurementioning

confidence: 99%

Automatic Transition Prediction and Application to Three-Dimensional High-Lift Configurations

Krumbein

2007

Journal of Aircraft

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A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and two e N -database methods for the prediction of transition due to Tollmien-Schlichting and crossflow instabilities were coupled to be applied to 3-D high-lift aircraft configurations which are of industrial relevance. The first application of the coupled system to a wing-body configuration with a three-element wing consisting of slat, main wing, and flap is described and documented in this paper. The prediction of the laminar-turbulent transition lines was done in a fully automatic manner. It will be shown that complex aircraft configurations can be handled without a priori knowledge of the transition characteristics of the specific flow problem. The computational results are compared with experimental data. Nomenclature b = semispan c = local chord length c p = pressure coefficient k cyc = number of RANS cycles for the transition location iteration, which represents the interval between two calls of the transition prediction module n T = global number of transition points Tu = turbulence intensity x = longitudinal coordinate of the configuration in the global coordinate system of the RANS solver x T = longitudinal coordinate value of the transition point z = spanwise coordinate being perpendicular to the longitudinal axis = angle of attack = value of the intermittency F = flap deflection angle S = slat deflection angle = nondimensional spanwise coordinate Subscripts CF = crossflow crit = critical j = counter of the transition points TS = Tollmien-Schlichting 1 = freestream value

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Section: Transition Prediction Coupling Structurementioning

confidence: 99%

Automatic Transition Prediction and Application to Three-Dimensional High-Lift Configurations

Krumbein

2007

Journal of Aircraft

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“…Here, converged force coefficients are not sufficient because the boundary-layer profiles still change significantly for many more iterations. Instead, the residuals have to be converged sufficiently to ensure fully developed boundarylayer profiles [35,36]. Figure 3 shows a typical convergence history for a RANS simulation on three multigrid levels.…”

Section: B Converging Laminar-turbulent Boundary Layermentioning

confidence: 99%

Automatic Transition Prediction in a Navier–Stokes Solver Using Linear Stability Theory

Fischer¹,

Soemarwoto²,

Weide

2021

AIAA Journal

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“…Thus, as shown in [6], the large number of grid points near the wall for a high resolution of the boundary layers, the adaptation of the Navier-Stokes grid in the laminar, turbulent and transitional boundary-layer regions and the generation of new adapted grids for the RANS solver after every step of the transition location iteration are avoided and the computational time can be massively reduced. In addition, the number of RANS iteration cycles between two steps of the transition location iteration can be highly reduced compared to an approach where the boundary-layer parameters are computed directly from the RANS grid [38]- [39], because the surface pressure converges significantly faster in the RANS computation than the boundarylayer velocity profiles [24], [29]- [30] which are the basis for the computation of the boundary-layer parameters. Because the laminar separation point is used as an approximation of the real transition point in the case that the e Nmethods do not detect transition upstream of the separation, this approach may fail when transition occurs inside a laminar separation bubble.…”

Section: Transition Prediction Coupling Structurementioning

confidence: 99%

Application of a Hybrid Navier-Stokes Solver with Automatic Transition Prediction

Krumbein

Krimmelbein

Schrauf

2007

25th AIAA Applied Aerodynamics Conference

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A hybrid Reynolds-averaged Navier-Stokes solver, a laminar boundary layer code and a fully automated local, linear stability code were coupled in order to predict the laminar-turbulent transition due to Tollmien-Schlichting and cross flow instabilities using the e N-method based on the two N factor approach. The coupled system was designed to be applied to three-dimensional aircraft configurations which are of industrial relevance. The application of the system to a two-dimensional two-element airfoil configuration and a threedimensional generic full aircraft configuration is described and documented in this paper. The prediction of the laminar-turbulent transition lines was done in a fully automatic manner. It will be shown that complex aircraft configurations can be handled without a priori knowledge of the transition characteristics of the specific flow problem. The computational results are partially compared to experimental data.

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Automatic Transition Prediction for High-Lift Systems Using a Hybrid Flow Solver

Cited by 12 publications

References 15 publications

Automatic Transition Prediction and Application to Three-Dimensional High-Lift Configurations

Automatic Transition Prediction and Application to Three-Dimensional High-Lift Configurations

Automatic Transition Prediction in a Navier–Stokes Solver Using Linear Stability Theory

Application of a Hybrid Navier-Stokes Solver with Automatic Transition Prediction

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