Add to ORKGNumerical simulations of the DLR F11 high lift half model in landing configuration in the test section of the ETW wind tunnel have been carried out with the unstructured CFD code DLR TAU. The numerical results are compared to measurements of the cryogenic wind tunnel ETW performed within the EU project FLIRET. The tests have been conducted with three different peniche heights of the F11 model to determine the influence of the so called half model mounting effects on the aerodynamic characteristics of model flow. Based on the numerical simulation of the half model tests the peniche effects and the wind tunnel flow itself are analyzed. The capability of the used CFD code for high Reynolds number testing is demonstrated
The paper describes numerical studies by DLR devoted to the computation of the DLR F-11 high lift co...
The paper describes the numerical study of the high-speed leg of the NASA Langley 14 by 22-foot Low ...
In this paper, we discuss how CFD may be used for better understanding of wind tunnel tests. Three e...
The objective of the joint research project HINVA (High-Lift In-Flight Validation) funded by the Ger...
The contribution of DLR to the numerical flow simulation activities "assessment and improvement...
In this paper a new approach of CFD supported wind tunnel testing is presented based on investigatio...
A major aim of the EC funded project DeSiReH (Design, Simulation and Flight Reynolds Number testing ...
Abstract: A peniche is designed to offset a half-span aircraft model from the wind tunnel wall bound...
A peniche is designed to offset a half-span aircraft model from the wind tunnel wall boundary layer....
In response to the 2nd AIAA CFD High Lift Prediction Workshop, the DLR-F11 wind tunnel model is anal...
Accurate measurementsof the aerodynamic performance in wind tunnel experiments require to retain dyn...
This paper discusses a CFD procedure for simulating open wind tunnel test sections based on the inve...
Abstract. This contribution highlights development, validation, and application of European CFD code...
AbstractSome years ago the national CFD project MEGAFLOW was initiated in Germany to combine many of...
The DLR F11 half-model was tested in the European Transonic Windtunnel ETW. The main emphasis of the...
The paper describes numerical studies by DLR devoted to the computation of the DLR F-11 high lift co...
The paper describes the numerical study of the high-speed leg of the NASA Langley 14 by 22-foot Low ...
In this paper, we discuss how CFD may be used for better understanding of wind tunnel tests. Three e...
The objective of the joint research project HINVA (High-Lift In-Flight Validation) funded by the Ger...
The contribution of DLR to the numerical flow simulation activities "assessment and improvement...
In this paper a new approach of CFD supported wind tunnel testing is presented based on investigatio...
A major aim of the EC funded project DeSiReH (Design, Simulation and Flight Reynolds Number testing ...
Abstract: A peniche is designed to offset a half-span aircraft model from the wind tunnel wall bound...
A peniche is designed to offset a half-span aircraft model from the wind tunnel wall boundary layer....
In response to the 2nd AIAA CFD High Lift Prediction Workshop, the DLR-F11 wind tunnel model is anal...
Accurate measurementsof the aerodynamic performance in wind tunnel experiments require to retain dyn...
This paper discusses a CFD procedure for simulating open wind tunnel test sections based on the inve...
Abstract. This contribution highlights development, validation, and application of European CFD code...
AbstractSome years ago the national CFD project MEGAFLOW was initiated in Germany to combine many of...
The DLR F11 half-model was tested in the European Transonic Windtunnel ETW. The main emphasis of the...
The paper describes numerical studies by DLR devoted to the computation of the DLR F-11 high lift co...
The paper describes the numerical study of the high-speed leg of the NASA Langley 14 by 22-foot Low ...
In this paper, we discuss how CFD may be used for better understanding of wind tunnel tests. Three e...