elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

Huber, Kerstin Claudie and Schütte, Andreas and Rein, Martin (2012) Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration. American Institute of Aeronautics and Astronautics, 30th Applied Aerodynamics Conference, 25.-28. Jun. 2012, New Orleans, Louisiana, USA.

[img]
Preview
PDF
6MB

Abstract

The numerical investigations of a generic UCAV configuration are presented. These investigations are part of the DLR internal project UCAV-2010. Compressible speed conditions are considered and presented. The DLR-F17E UCAV configuration is a flying lambda delta wing with sweep angle of 53° and varying leading edge radius. The flow field of this UCAV configuration is dominated by vortex structures and vortex-to-vortex interaction. The paper aims to give a comparison between numerical- and experimental investigations in order to gain a deeper understanding of the complex flow physics. Furthermore, it will highlight the influence of Mach- and Reynolds number change on the flow and the overall aerodynamic behavior of the configuration. The DLR TAU-Code is used to simulate the flow field, using an unstructured grid and the turbulence model of Spalart-Allmaras. Forces and moment measurements taken in the DNW-TWG, Göttingen, on the DLR-F17E configuration serve as the experimental basis to validate the numerical findings. Findings on the SACCON configuration serve as a comparison case aiming to show possible portability between different model scales but also to find analogies between low speed (M=0.15) and compressible speed (M=0.5) scenarios. This paper builds up upon the finding within the NATO/RTO AVT-161 Research Task Group on “Assessment and Control Predictions for NATO Air and Sea Vehicles” and its findings shall serve as a basis for further experimental investigations of medium to high speed wind tunnel experiments. Furthermore, this paper addresses the importance of understanding and the ability to predict controlled- and uncontrolled flow separation and the interaction of vortex systems in order to estimate the aerodynamic behavior within the entire flight envelope and to meet Stability- and Control needs.

Item URL in elib:https://elib.dlr.de/78407/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Huber, Kerstin Claudiekerstin.huber (at) dlr.deUNSPECIFIED
Schütte, Andreasandreas.schuette (at) dlr.deUNSPECIFIED
Rein, Martinmartin.rein (at) dlr.deUNSPECIFIED
Date:28 June 2012
Refereed publication:No
Open Access:No
In DOAJ:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Delta Wing, CFD, Vortex, Wind tunnel Experiment
Event Title:American Institute of Aeronautics and Astronautics, 30th Applied Aerodynamics Conference
Event Location:New Orleans, Louisiana, USA
Event Type:international Conference
Event Dates:25.-28. Jun. 2012
Organizer:AIAA - American Institute of Aeronautics and Astronautics
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 , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Transport Aircraft
Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Huber, Kerstin Claudie
Deposited On:15 Nov 2012 11:16
Last Modified:12 Dec 2013 21:50

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.