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DLR Results from the Fourth AIAA Computational Fluid Dynamics Drag Prediction Workshop

Brodersen, Olaf and Crippa, Simone and Eisfeld, Bernhard and Keye, Stefan and Geisbauer, Sven (2014) DLR Results from the Fourth AIAA Computational Fluid Dynamics Drag Prediction Workshop. Journal of Aircraft, 51 (4), pp. 1135-1148. American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/1.C031533 ISSN 0021-8669

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Official URL: http://arc.aiaa.org/doi/abs/10.2514/1.C031533

Abstract

A summary about the DLR, German Aerospace Center results from the fourth AIAA Computational Fluid Dynamics Drag Prediction Workshop is presented. Compared to the investigations in the previous three workshops, the latest workshop had a stronger focus on drag and trim drag predictions as well as pitching moment calculations. Therefore, the new Common Research Model developed by NASA’s Subsonic Fixed Wing Aerodynamics Technical Working Group and tested in NASA wind tunnels is used. It represents a state-of-the-art transonic transport aircraft configuration, and in contrast to the configurations previously taken, it includes an optional horizontal tailplane with three different tail settings. DLR has defined three objectives for its activities in the fourth drag prediction workshop. At first, investigations should identify solution accuracy and grid convergence behavior using prismatic element dominant grids for boundary-layer resolution in comparison to hexahedral element dominant grids. Second, the influence of turbulence models of increasing complexity is of interest regarding transonic pressure distributions and flow separations. Therefore, the one-equation turbulence model of Spalart and Allmaras, the two-equation Menter kω-shear-Stress-transport model, and the Speziale–Sarkar–Gatski/Launder–Reece–Rodi–ω Reynolds-stress model are applied. The third objective is to analyze what differences in the calculated pitching moments and horizontal tailplane trim angles can be expected for the Common Research Model with different horizontal tailplane settings when grids are regenerated for each setting or when they are deformed iteratively based on the grid for the initial setting. All investigations are performed with the grid generation software Solar and Centaur™ and the Reynolds-averaged Navier–Stokes solver TAU. Recently, selected experimental data have been released by NASA and are used here for comparisons.

Item URL in elib:https://elib.dlr.de/90159/
Document Type:Article
Title:DLR Results from the Fourth AIAA Computational Fluid Dynamics Drag Prediction Workshop
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Brodersen, OlafO.Brodersen (at) dlr.deUNSPECIFIED
Crippa, Simonesimone.crippa (at) airbus.comUNSPECIFIED
Eisfeld, Bernhardbernhard.eisfeld (at) dlr.deUNSPECIFIED
Keye, Stefanstefan.keye (at) dlr.deUNSPECIFIED
Geisbauer, Svensven.geisbauer (at) dlr.deUNSPECIFIED
Date:July 2014
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:51
DOI :10.2514/1.C031533
Page Range:pp. 1135-1148
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
ISSN:0021-8669
Status:Published
Keywords:Aerodynamics CFD Drag Prediction Workshop
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Simulation and Validation
Location: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Transport Aircraft
Institute of Aerodynamics and Flow Technology > C²A²S²E - Center for Computer Applications in AeroSpace Science and Engineering
Deposited By: Brodersen, Dr.-Ing. Olaf
Deposited On:08 Sep 2014 14:11
Last Modified:08 Mar 2018 18:41

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