Titlebook: New Results in Numerical and Experimental Fluid Mechanics VII; Contributions to the Andreas Dillmann,Gerd Heller,Wolfgang Schröder Conferen

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Panther

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Adherent

Application of a New Roughness Extension for , − , Turbulence Modelsa flat plate and around the NACA 65.-215 airfoil with a rough surface. The results are compared to predictions using the boundary condition originally devised by Wilcox [11] for rough surfaces, and to predictions with the Spalart-Allmaras model with the Boeing roughness extension by Aupoix and Spala

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Improved Wall Functions Based on the 1D Boundary Layer Equations for Flows with Significant Pressureequations for wall-parallel velocity, including pressure gradient term and convective term, and turbulence quantities in wall normal direction. For each wall node, this system of equations is integrated numerically on an embedded subgrid between wall node and first node above the wall. The method is

employor

A Wall Model Based on Simplified Thin Boundary Layer Equations for Implicit Large Eddy Simulation ofyer Equations (TBLE) is designed and applied to turbulent channel flow for a wide range of friction Reynolds numbers up to .. =20,000. The prediction capability of the employed wall model concerning mean velocities and Reynolds stresses is satisfactory, even on very coarse LES grids. The coupling po

Impugn

Detached-Eddy Simulation of Supersonic Flow Past Cylindrical Aft Body with and without Base Bleed end, simulations are performed using detached-eddy simulation. To evaluate the performance of DES, numerical predictions are compared with computations based on RANS and experimental data for the base flow without bleed. To understand the influence of the bleed on the flow and the base pressure dis

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Prediction of the Wind Tunnel Sidewall Effect for the iGREEN Wing-Tailplane Interference Experimentde-wall. Results show that the effect of the sidewalls is similar to an offset in the angle of attack (but can only partially be corrected by a change in .), and that this effect is proportional to the lift and Mach number. These results were used in the design phase for the iGREEN wing-tailplane in

hurricane

The Influence of the Length Scale Equation on the Simulation Results of Aerodynamic Flows Using Diffequation, have been applied to the transonic flow around the RAE 2822 airfoil and the ONERA M6 wing. Comparison with the Wilcox . – . model shows the influence of replacing the .-equation and the Boussinesq hypothesis by the modeled Reynolds stress transport equation. Particularly for the M6 wing di

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Efficient Flow Computation Including Turbulent Transportgrid framework. In previous investigations [7,8,10], the algebraic model of Baldwin and Lomax [1] was employed as turbulence model. In the present contribution, this model is replaced by the model of Spalart and Allmaras [9], where an additional partial differential equation has to be solved. The de