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Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

Huber, Kerstin Claudie (2010) Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration. DLR-Interner Bericht. DLR-IB 124-2010/4, 105 S.

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The main objective of this study is to contribute towards a more comprehensive understanding of the vortex dominated flow over the DLR-F17E configuration with varying leading edge radii as part of the DLR UCAV2010 project. The vortical flow over sharp edges delta wings is mainly understood though the need has arisen to further extend the knowledge about the vortex system behaviour over blunt edged delta wings. This work aims to determine the effect of Reynolds number and Mach number variation over the DLR-F17E configuration. For the numerical investigation the DLR flow solver TAU, solving for the compressible, three-dimensional, time-accurate Reynolds-Averaged Navier-Stokes equations, is used. The configuration was meshed using the unstructured-hybrid grid generator Centaur. Experimental data on the SACCON in the NWB Braunschweig, gathered prior to this work, serves as comparative data for the numerical outcomes. For low Mach numbers at low angles of attack the numerical outcomes matched the experiment data quite well. However for higher angles of attack the flow solver failed to give a near real world representation of the vortex systems as observed during the experiment. With increasing angle of attack the tip vortex moves towards the apex and at high angles of attack a large high suction region over the entire wing is observed. Further it was found that with increasing Mach number the apex vortex gains in strength and the tip vortex moves towards the apex. The tip vortex develops to a huge outer vortex which introduces a high suction area initializing a nose down pitching moment of the configuration at M=0.4 up to M=0.6. The Reynolds number effect on the configuration was found to be minor. Though, it was possible to determine that the tip vortex gains in strength with increasing Reynolds number. Also the tip vortex slightly increased its size towards the trailing edge with increasing Reynolds number. Experimental investigations on the DLR-F17E model are currently being planned in order to compare these here conducted numerical results, as part of the FaUSST project. Furthermore numerical investigations using the cell-centered approach are being conducted.

Item URL in elib:https://elib.dlr.de/72000/
Document Type:Monograph (DLR-Interner Bericht)
Title:Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Huber, Kerstin Claudiekerstin.huber (at) dlr.deUNSPECIFIED
Date:August 2010
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Number of Pages:105
Keywords:CFD, vortex dominated flow, delta wing
Institution:Royal Institut of Technology (KTH) / DLR - Institut für Aerodynamik und Strömungsmechanik
Department:Department of Aeronautical and Vehicle Engineering / Abteilung Transportflugzeuge
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Simulation & Validation (old)
Location: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Transport Aircraft
Deposited By: Huber, Kerstin Claudie
Deposited On:29 Nov 2011 09:24
Last Modified:29 Nov 2011 09:24

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