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Stability and Control Investigations of Generic 53 Degree Swept Wing with Control Surfaces

Schütte, Andreas and Huber, Kerstin Claudie and Frink, Neal T. and Boelens, Okko J. (2016) Stability and Control Investigations of Generic 53 Degree Swept Wing with Control Surfaces. Journal of Aircraft, 55 (2), pp. 502-533. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.C033700. ISSN 0021-8669.

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Official URL: https://doi.org/10.2514/1.C033700


A contribution for the assessment of the static and dynamic aerodynamic behavior of a generic unmanned combat air vehicle configuration with control devices using computational fluid dynamics methods is given. For the study, various computational approaches have been used to predict stability and control parameters for aircraft undergoing nonlinear flight conditions. For the computational fluid dynamics simulations, three different computational fluid dynamics solvers are used: the unstructured grid-based solvers DLR TAU code and USM3D from NASA, as well as the structured grid-based National Aerospace Laboratory/NLR solver ENSOLV. The numerical methods are verified by experimental wind-tunnel data. The correlations with experimental data are made for static longitudinal/lateral sweeps and at varying frequencies of prescribed roll/pitch/yaw sinusoidal motions for the vehicle operating with and without control surface deflections. Furthermore, the investigations should support the understanding of the flow physics around the trailing-edge control devices of highly swept configurations with a vortex-dominated flowfield. Design requirements should be drawn by analyzing the interaction between the vortical flow and the control devices. The present work is part of the North Atlantic Treaty Organization’s Science and Technology Organization/ Applied Vehicle Technology Task Group AVT-201 on stability and control prediction methods´.

Item URL in elib:https://elib.dlr.de/105801/
Document Type:Article
Title:Stability and Control Investigations of Generic 53 Degree Swept Wing with Control Surfaces
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Schütte, Andreasandreas.schuette (at) dlr.deUNSPECIFIED
Huber, Kerstin Claudiekerstin.huber (at) dlr.deUNSPECIFIED
Frink, Neal T.Neal.T.Frink (at) nasa.govUNSPECIFIED
Boelens, Okko J.Okko.Boelens (at) nlr.nlUNSPECIFIED
Date:29 March 2016
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.2514/1.C033700
Page Range:pp. 502-533
EditorsEmailEditor's ORCID iD
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:UCAV, vortical flow, control devices, NATO STO AVT, NLR, NASA, TAU-Code, Ensolv, USM3D
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 - Military Technologies (old)
Location: Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Transport Aircraft
German-Dutch Windtunnels
Deposited By: Schütte, Andreas
Deposited On:22 Aug 2016 11:27
Last Modified:05 Nov 2020 20:56

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