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

ligature

Application of the Multi-Scale-Finite-Volume Method to the Simulation of Incompressible Flows with Ilting Poisson equation is formally identical to the elliptic problems governing flows in porous media. An efficient iterative procedure for the computation of the pressure is then obtained by adapting the iterative-multi-scale-finite-volume procedure by Hajibeygi et al. [2].

Admonish

Cocker

Offensive

Detached-Eddy Simulation of Supersonic Flow Past Cylindrical Aft Body with and without Base Bleedns 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 distribution, predictions of the base flow with bleed are compared with numerical data of the case without bleed.

易改变

Automatic Transition Prediction for Three-Dimensional Aircraft Configurations Using the DLR , Codeons during the ongoing flow computation. The procedure is applied to a three-dimensional wing-body configuration and the sensitivity of the coupled system to a variety of coupling parameters is investigated.

憎恶

An Approach to the Gust Problem with Interfering Profilesdy wake of the leading profile encounters the trailing profile and effects a load change. A first simplified attempt has been made using a rigid grid where both profiles execute a synchronous heaving motion.

Spartan

仲裁者

A Wall Model Based on Simplified Thin Boundary Layer Equations for Implicit Large Eddy Simulation ofsition between the simplified TBLE model and the LES should be located at the bottom of the logarithmic region. The grid resolution requirement depends mainly on the embedded TBLE grids and is only weakly dependent on the Reynolds number.

alleviate

esoteric

Numerical Simulation of the Elastic and Trimmed Aircraft-structure interaction (FSI) procedure uses a partitioned approach to compute the flow around the configuration in static aeroelastic equilibrium. This simulation environment has been successfully applied to trim a rigid transportaircraft configuration in viscous flow as well as in inviscid flow with rigid and flexible wing.