Flow Modulation and Fluid—Structure Interaction at Airplane Wings: Research Results of the Collaborative Research Center SFB 401 at RWTH Aachen, University of Technology, Aachen, Germany

398 Pages·2003·13.93 MB·English

by  Professor Dr. Josef Ballmann (auth.)

84 Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM)
Editors
E. H. HirschelIMünchen
K. FujiilKanagawa
w.
HaaselMünchen
B. van Leer/Ann Arbor
M. A. Leschziner/London
M. Pandolfi/Torino
J. Periaux/Paris
A. Rizzi/Stockholm
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Flow Modulation and Fluid-Strueture
Interaction at Airplane Wings
Research Results of the Collaborative Research Center
SFB 401 at RWTH Aachen, University ofTechnology,
Aachen, Germany
Josef Ballmann (Editor)
, Springer
Professor Dr. Josef Ballmann
RWTHAachen
Lehr-und Forschungsgebiet Mechanik
Templergraben 64
D -52062 Aachen
Germany
ISBN 978-3-642-53613-7 ISBN 978-3-540-44866-2 (eBook)
DOI 10.1007/978-3-540-44866-2
Library of Congress Cataloging-in-Publication-Data
Flow modulation and f1uid-structure interaction at airplane wings : research results of the collabo
rative research center SFB 401 at RWTH Aachen, University ofTechnology, Aachen, Germany I
JosefBallmann (editor).
p. cm. --(Notes on numerical fluid mechanics and multidisciplinary design; v. 84)
Includes bibliographical references.
1. Air f1ow. 2. Airplanes --Wings. 3. Aerodynamics. I.Ballmann, Josef. H. Rheinisch-Westfälische
Technische Hochschule Aachen. IH. Notes on numerical fluid mechanics and multidisciplinary
design; v. 84)
TL574.F5F582003
629.132'32--dc21
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NNFM Editor Addresses
Prof. Dr. Ernst Heinrich Hirschel Prof. Dr. Maurizio Pandolfi
(General editor) Politecnico di Torino
Herzog-Heinrich-Weg 6 Dipartimento di Ingegneria
D-85604 Zorneding Aeronautica e Spaziale
Germany Corso Duca degli Abruzzi, 24
E-mail: [email protected] 1- 10129 Torino
Italy
Prof. Dr. Kozo Fujii E-mail: [email protected]
Space Transportation Research
Division Prof. Dr. Jacques Periaux
The Institute of Space Dassault Aviation
and Astronautical Science 78, Quai Marcel Dassault
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Kanagawa,229-851O France
Japan E-mail: [email protected]
E-mail: [email protected]
Prof. Dr. Arthur Rizzi
Dr. Werner Haase Department of Aeronautics
Höhenkirchener Str. 19d KTH Royal Institute of Technology
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Germany S-10044 Stockholm
E-mail: [email protected] Sweden
E-mail: [email protected]
Prof. Dr. Bram van Leer
Department of Aerospace Engineering Dr. Bernard Roux
The University of Michigan L3M - IMT La Jetee
Ann Arbor, MI 48109-2140 Technopole de Chateau-Gombert
USA F-13451 Marseille Cedex 20
E-mail: [email protected] France
E-mail: [email protected]
Prof. Dr. Michael A. Leschziner
Imperial College of Science,
Technology and Medicine
Aeronautics Department
Prince Consort Road
London SW7 2BY
U.K.
E-mail: [email protected]
v
PREFACE
The research work of the collaborative research center SFB401 Flow Modulation
and Fluid-Structure Interaction at Airplane Wings at the Rheinisch-Westfälische
Technische Hochschule (RWTH) Aachen, which is reported in this book, was pos
sible due to the financial support of the Deutsche Forschungsgemeinschaft (DFG).
The proposal has been approved after evaluation by the referees of DFG selected
from other universities and industry, which is gratefully acknowledged. The work
is still in progress and now approved to continue until the end of year 2005.
More than 50 scientists from universities of the United States, Russia, France, Italy,
Japan, Great Britain, Sweden, Netherlands, Switzerland, Austria and research orga
nizations NASA, ONERA, NLR, DLR could be invited and have visited the research
center, gave seminars on their research on related topics and some of them stayed
longer for joined work.
Besides its scientific value, also the importance of the pro gram for scientific educa
tion becomes evident by looking at the numbers of completed theses, which are up
to now about 15 doctoral theses, 40 diploma theses and 70 study theses.
The authors of this book acknowledge the valuable support coming from all these
persons and institutions. They are especially grateful to the referees having reviewed
this work, A. Cohen (Universite Pierre et Marie Curie), J. Cooper (Manchester
School of Engineering), W. Devenport (Virginia Tech.), M. Drela (MIT), F. Gern
(Avionics Specialties Inc.), A. Griewank (TU Dresden), H. Hönlinger (DLR), P.
Hovland (Argonne National Laboratory), F. Menter (AEA Technology), M. Pandolfi
v.J.
(Politecnico di Torino), Rossow (NASA Ames), G. Schewe (DLR), F. Seiler
(ISL), T. Sonar (TU Braunschweig), S.P. Spekreijse (NLR), LW. Tjatra (NLR), H.
Tijdeman (University of Twente), R. Voss (DLR), P. Wernert (ISL), for the valuable
time they spent to improve the papers collected in this volume.
Furthermore, it is the desire of the authors to express their deep gratitude to Dr.
Dieter Funk from Deutsche Forschungsgemeinschaft for all his valuable suggestions
and the competent guidance during all processes related to the funding.
Finally, the editor gives thanks to his students Frank Bramkamp, Carsten Braun and
Michael Hesse who did the technical editing work and last but not least to Professor
E.H. Hirschel and Springer Verlag who made this edition possible in the series Notes
on Numerical Fluid Mechanics and Multidisciplinary Design.
Aachen, January 2003
Josef Ballmann
(Co-ordinator of SFB401)
VII
CONTENTS
1 Introduction 1
2 Model Flow, Wakes and Vortices in High Lift Configuration 5
2.1 Experimental Analysis and Modulation of Vortices
E. Özger, l. Schell, D. Jacob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
2.2 Simulation of Vortex Sheets at Take-Off and Landing
l. Schell, E. Özger, D. Jacob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
2.3 Analysis of Wakes and Wake-Jet Interaction
E. Fares, W. Schröder ..................................... 57
2.4 Aerodynamic Design of Transonic Adaptive Airfoils with Natu-
ral Transition 85
A. Meijering, W. Limberg, W. Schröder ..................... .
2.5 Experiments in a Transonic Shock Tube at High Mach and
Reynolds Numbers
Th. ReicheI, M. Zechner, H. Olivier . . . . . . . . . . . . . . . . . . . . . . . . . 105
3 Numerical Tools and Approaches for Flow Simulation
with Local Adaptivity 123
3.1 H-Adaptive Multiscale Schemes for the Compressible Navier
Stokes Equations -Polyhedral Discretization, Data Compression
and Mesh Generation
F. Bramkamp, B. Gottschlich-Müller, M. Hesse, Ph. Lamby,
S. Müller, J. Ballmann, K.H. Brakhage, W. Dahmen ........... 125
3.2 Automated Gradient Calculation
CH. Bischof, H.M. Bücker, B. Lang, A. Rasch. . . . . . . . . . . . . . . . 205
4 Computational and Experimental Aeroelasticity 225
4.1 On Well-Posedness and Modelling for Nonlinear Aeroelasticity
R. Massjung, J. Hurka, W. Dahmen, J. Ballmann ............. 227
4.2 Concepts for Reduced Structural Models of Airplane Wings in
Aeroelasticity
W. Jung, H.-G. Reimerdes .................................. 249
4.3 Computational Aeroelasticity with Reduced Structural Models
G. Britten, C Braun, M. Hesse, J. Ballmann ... . . . . . . . . . . . . . . 275
4.4 Approximated Nonlinear Stability Analysis of the Dynamics of
Flexible Aircraft
N. Siepenkötter, W. Kasberg, W. Alles. . . . . .. . . . . . . . . . . . . . . . . 301
IX
4.5 Analysis of Unsteady Airfoils at Low Speeds
x. Bertrdn, H. Olivier, S. Turek . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 323
4.6 Experiments on Transonic Aerodynamics about Elastically Sus
pended Airfoils
C. Hillenherms, W. Schröder, W. Limberg . . . . . . . . . . . . . . . . . . . . 351
4.7 Design, Qualification and Experimental Investigation on Flexi-
ble Wind-Tunnel Wing Models
M. Kämpchen, H. Korsch, A. Dafnis, H.-G. Reimerdes ........ 377
x
I.Introduction
The Collaborative Research Center SFB 401: Flow Modulation and Fluid-Structure
Interaction at Airplane Wings is concemed with fundamental problems of very high
capacity aircrafts with large elastic wings designated for transonic transport. This
volume presents a survey of the current research of the center from the first up to
the fifths year, with emphasis on the results achieved so far.
The content of the three chapters following this introduction correspond to the three
main topics of large transport aircrafts, wh ich the center concentrates on: (i) Model
fiow, wakes and vortices of airplanes in high lift configuration, (ii) Numerical tools
for large scale adaptive fiow simulation based on multi sc ale analysis and a paramet
ric mappil}g concept for grid generation, and (iii) Validated computational design
tools based on direct aeroelastic simulation with reduced structural models.
On these topics fundamentals and methods for fiow modulation, the physical and
mathematical modeIling, the mathematical well-posedness and the numerical solu
tion are elaborated in altogether 14 projects in cooperation of the departments for
Aircraft Design and Aeronautics (ILR), Aerodynamics (AIA), Lightweight Struc
tures (IfL), Flight Dynamics (FD), Mathematics and Numerical Mathematics
(IGPM), Scientific Computing (SC), and Mechanics (LFM), all at RWTH Aachen,
University of Technology. All mathematicaVnumerical efforts are joined by experi
mental analysis in the full range of Mach and Reynolds numbers. For experimental
analysis water tunnels, low speed wind tunnels and transonic wind and shock tun
nels are employed.
The Collaborative Research Center has defined a reference configuration with a
supercritical profile, which is based on the three-element high-lift airfoil system
BAC3-11IRES/30/21 (described in AGARD-AR 303).
The first two contributions of Chapter 2 are concemed with design features mini
mizing the hazard by the vortex system wh ich is generated by very large aircrafts
during take-off and landing for following aircrafts. This purpose requires the knowl
edge of the vortical fiow field within a distance up to 100 spans behind the airplane.
Presently, neither large scale wind tunnel measurements nor numerical Navier
Stokes sol vers can provide the necessary data without an extreme effort. There
fore, it is useful to choose a water tunnel as experimental facility which is now
available in the center for small scale wake investigations in a distance of up to 60
spans. In this context it seems also advisable to apply available vortex transport
methods in reduced dimensions for layout of test configurations and measurement
interpretation. Nevertheless, at least in the near wake wind tunnel measurements
together with the most sophisticated available Navier-Stokes sol ver have to be ap
plied. The third contribution of Chapter 2 is concemed therewith. Furthermore, it
provides improved turbulence modeIling and novel boundary conditions and simu-
J. Ballmann (ed.), Flow Modulation and Fluid—Structure Interaction at Airplane Wings
© Springer-Verlag Berlin Heidelberg 2003
lation techniques for the analysis of the near wake and wake-jet interaction behind
high-lift configurations. The fourth and fifth contributions of this chapter consider
transonic flow experimentally and numerically. The first one is concerned with the
optimum design of an adaptive airfoil with respect to viscous drag reduction by
downstream displacement of transition in the transonic regime. The other describes
a new transonic shock tunnel for high Reynolds number flow corresponding to real
flight conditions. The facility has been developed and built in the center and is now
operating up to Rec = 40 . 106 at transonic speeds. First results are presented.
Chapter 3 faces the challenge to essentially improve the quality of numerical solu
tions and to include later on the aeroelastic quality into the design processes of the
aerodynamic shape and the supporting structure. For these tasks large sc ale simu
lations of compressible fluid flow and fluid-structure interaction are required. The
first paper of Chapter 3 reports the present state in the development of the new sol ver
QUADFLOW for this purpose. The method is developed by a group of mathemati
cians and engineers. In order to keep the size of the discrete problems at every stage
as small as possible for any given target accuracy, a multi-resolution local adaptation
strategy is employed. The aim is a solution method which automatically detects all
relevant flow features such as shocks and shear layers in flows about complex con
figurations even when starting the computation on a very coarse grid and without
any knowledge about the expected flow field. A mesh generation concept has been
introduced that is to support the adaptive strategy as well as possible. One of its key
ideas is to understand meshes as parametrie mappings determined by possibly few
control points, as opposed to storing every mesh cell separately. A mapping based
on B-Splines with low number of control points allows for a surface conforming
grid evaluation. An unstructured finite volume discretization is employed which is
capable to operate on meshes with hanging nodes, occurring due to the local mesh
adaptation. In the presented state of development, the method has proven to apply
excellently for shock configurations, as e.g. the famous fish-tail shock formation
at the NACAOO12 airfoil, and for shear and boundary layers as well. The second
contribution of the chapter reports on automatie differentiation, wh ich is used to
calculate sensitivities of flow solutions with respect to parameters as e.g. Mach
number, angle of attack or surface shape parameters. It can also be used to eval
uate Jacobi matrices arising in implicit flow solvers. A key feature is its ability to
generate accurate derivatives rather than approximations obtained from numerical
differentiation by use of divided differences.
Chapter 4 is devoted to computational and experimental aeroelasticity. In the first
contribution, which is fundamental for computational aeroelasticity, well-posedness
and modelling of nonlinear aeroeiasticity is considered. An elastic panel in transonic
flow was chosen as a model problem for mathematical analysis and computational
experiments. Based on energy methods a uniqueness proof for small times has been
established. In that context the energy transfer between structure and fluid became
evident as an essential feature. As a consequence, independently of possibly dif
ferent discretizations in the fluid and in the structural domain, it is very important
to simulate the energy transfer between the different phases in the discretized sys-
2