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Numerical Simulation of Manoeuvring Aircraft by Aerodynamic and Flight-Mechanic Coupling

Schütte, Andreas and Einarsson, Gunnar and Madrane, A. and Schöning, Britta and Mönnich, Wulf and Krüger, Wolf R. (2003) Numerical Simulation of Manoeuvring Aircraft by Aerodynamic and Flight-Mechanic Coupling. In: NATO RTO-AVT Meeting Proceedings, RTO-MP-089. NATO RTO - Research and Technology Organisation. RTO-AVT Symposium on "Reduction of Military Vehicle Acquisition Time and Cost through Advanced Modelling and Virtual Simulation", 22.-25.4.2002, Paris, France. doi: 10.14339/RTO-MP-089. ISBN 92-837-0027-9.

Full text not available from this repository.

Official URL: https://www.sto.nato.int/publications/STO%20Meeting%20Proceedings/RTO-MP-089/MP-089-$$ALL.pdf


This paper presents results of simulations performed within the scope of the DLR-Project AeroSUM- “Aerodynamic Simulation of Unsteady Manoeuvres”. The objective of the AeroSUM-Project is to develop a numerical tool to simulate the unsteady aerodynamics of a free flying aircraft, by use of coupled aerodynamic and flight-mechanic computations. To achieve this objective, the unstructured, time accurate CFD flow-solver Tau is coupled with a computational module solving the flight-mechanic equations of motion. By use of an overlapping grid technique (chimera), simulations of a complex configuration with movable control-surfaces is possible. Results of static calculations are presented to show the basic aerodynamics of the vortex dominated flowfield of the delta wing. The static simulation cases also serve as starting solutions for the unsteady simulations. Results of the unsteady manoeuvre simulations are divided into guided motion and freeflight motion. For the guided motion an oscillating motion with a given frequency and amplitude is presented. For the free-flight motion, the following cases are presented: free-to-roll from a non-zero initial roll-angle (without flap deflection), and free-to-roll initiated by flap deflection from an initial rollangle of zero. These calculations demonstrate the functionality of the simulation system. A 65-degree cropped delta wing model, with fuselage and movable trailing edge flaps, is used to gather experimental data. Several forced and free-to-roll experiments around the body fixed axes, both with and without flap deflection, are performed in order to validate the computational results obtained with the simulation tool.

Item URL in elib:https://elib.dlr.de/110868/
Document Type:Conference or Workshop Item (Speech)
Title:Numerical Simulation of Manoeuvring Aircraft by Aerodynamic and Flight-Mechanic Coupling
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Date:March 2003
Journal or Publication Title:NATO RTO-AVT Meeting Proceedings, RTO-MP-089
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Publisher:NATO RTO - Research and Technology Organisation
Keywords:delta wing, vortical flow, maneuver Simulation, CFD, flight mechanics coupling
Event Title:RTO-AVT Symposium on "Reduction of Military Vehicle Acquisition Time and Cost through Advanced Modelling and Virtual Simulation"
Event Location:Paris, France
Event Type:international Conference
Event Dates:22.-25.4.2002
Organizer:NATO RTO - Research and Technologie Organisation
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
Institute of Aerodynamics and Flow Technology > C²A²S²E - Center for Computer Applications in AeroSpace Science and Engineering
Institute of Flight Systems > Flight Dynamics and Simulation
Institute of Aeroelasticity > Loads Analysis and Aeroelastic Design
Deposited By: Schütte, Andreas
Deposited On:30 Jan 2017 09:54
Last Modified:30 Jan 2017 09:54

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