88880000 NNNNooootttteeeessss oooоnnnп NNNNuuuummmmeeeerrrriiiiccccaaaallll FFFFlllluuuuiiiidddd MMMMeeeecccchhhhaaaannnniiiiccccssss aaaannnndddd MMMMuuuullllttttiiiiddddiiiisssscccciiiipppplllliiiinnnnaaaarrrryyyy DDDDeeeessssiiiiggggnnnn ((((NNNNNNNNFFFFMMMM)))) EEEEddddiiiittttoooorrrrssss EEEЕ.... HHHН.... HHHНiiiirrrrsssscccchhhheeeeUUUUMMMMiiiiiiiinnnncccchhhheeeennnn KKKК.... FFFFuuuujjjjiiiiiiiil///KKKKaaaannnnaaaaggggaaaawwwwaaaa WWWW.... HHHHaaaaaaaasssseeee////MMMMiiiiiiiinnnncccchhhheeeennnn BBBВ.... vvvvaaaannnn LLLLeeeeeeeerrrr////AAAAnnnnnnnn AAAArrrrbbbboooorrrr MMMМ.... AAAА.... LLLLeeeesssscccchhhhzzzziiiinnnneeeerrrr////LLLLoooonnnnddddoooonnnn MMMМ.... PPPPaaaannnnddddoooollllffffiiii////TTTToooorrrriiiinnnnoooo JJJJ.... PPPPeeeerrrriiiiaaaauuuuxxxxl///PPPPaaaarrrriiiissss AAAА.... RRRRiiiizzzzzzzziiii////SSSSttttoooocccckkkkhhhhoooollllmmmm BBBВ.... RRRRoooouuuuxxxx///lMMMMaaaarrrrsssseeeeiiiilllllllleeee SSpprriinnggeerr--VVeerrllaagg BBeerrlliinn HHeeiiddeellbbeerrgg GGmmbbHH OONNLLIINNEE LLIIBBRRAARRYY EEnnggiinneeeerriinngg hhttttpp::////wwwwww..sspprriinnggeerr..ddee//eennggiinnee// DDrraagg RReedduuccttiioonn bbyy SShhoocckk aanndd BBoouunnddaarryy LLaayyeerr CCoonnttrrooll RReessuullttss ooff tthhee PPrroojjeecctt EEUURROOSSHHOOCCKK IIII SSuuppppoorrtteedd bbyy tthhee EEuurrooppeeaann UUnniioonn 11999966--11999999 EEggoonn SSttaanneewwsskkyy,, JJeeaann DDeelleerryy,, JJoohhnn FFuullkkeerr aanndd PPaaoolloo ddee MMaatttteeiiss ((EEddiittoorrss)) SSpprriinnggeerr Dr. Egon Stanewsky Prof. John Fulker DLR Institute of Aerodynamics QinetiQ Ltd. and Flow Technology Centre of Aerospace Technology Bunsenstr.10 Bedford MK41 6AE u.K. D -37073 G6ttingen Germany Dr. Paolo de Matteis Prof. Jean Delery CIRA Experimental ONERA FundamenallExperimental Aerodynamics Laboratories Aerodynamics Department Via Maiorise 8, rue des Vertugadins 1-81043 Capua (CE) F -92190 Meudon Italy France Library of Congress Cataloging-in-Publication Data applied for Die Deutsche Bibliothek -Cip-Einheitsaufnahme Drag reduction by shock and boundary layer control: results of the project EUROSHOCK II I Egon Stanewsky ... (ed.). -Springer-Verlag Berlin Heidelberg 2002 (Notes on numerical fluid mechanics and multidisciplinary design (NNFM) ; 80) (Engineering online library) ISSN 0179-9614 ISBN 978-3-642-07762-3 ISBN 978-3-540-45856-2 (eBook) DOI 10.1007/978-3-540-45856-2 This work is subject to copyright. All rights are reserved, whether the whole or part of the material is con cerned, specifically the rights of translation, reprinting, re-use of illustrations, recitation, broadcasting, reproduction on microfllms or in any other way, and storage in data banks. Duplication of this publication or parts thereof is permitted under the provisions of the German Copyright Law of September 9, 1965, in its current version, and permission for use must always be obtained from Springer-Verlag. Violations are liable for prosecution under the German Copyright Law. http://www.springer.de © Springer-Verlag Berlin Heidelberg 2002 Originally published by Springer-Verlag Berlin Heidelberg New York in 2002 Softcover reprint ofthe hardcover lst edition 2002 The use of general descriptive names, trademarks, etc. in this publication does not imply, even in the absence of a specific statement, that such names are exempt from the relevant protective laws and regulations and therefore free for general use. Cover design: de'blik, Berlin Printed on acid-free paper NNFM Editor Addresses Prof. Dr. Ernst Heinrich Hirschel Prof. Dr. Maurizio Pandolfi (General editor) Politecnico di Torino Herzog-Heinrich-Weg 6 Dipartimento di Ingegneria Aeronautica D-85604 Zorneding 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 The Institute of Space Prof. Dr. Jaques Periaux and Astronautical Science Dassault Aviation 3-1-1, Yoshinodai, Sagamihara, 78, Quai Marcel Dassault Kanagawa, 229-8510 F-92552 St. Cloud Cedex Japan France E-mail: [email protected] E-mail: [email protected] Dr. Werner Haase Prof. Dr. Arthur Rizzi Hohenkirchener Str. 19d Department of Aeronautics D-85662 Hohenbrunn KTH Royal Institute of Technology Germany Teknikringen 8 E-mail: [email protected] S-10044 Stockholm Sweden Prof. Dr. Bram van Leer E-mail: [email protected] Department of Aerospace Engineering The University of Michigan Dr. Bernard Roux Ann Arbor, MI 48109-2140 IRPHE-IMT USA Technopole de Chateau-Gombert E-mail: [email protected] F-13451 Marseille Cedex 20 France Prof. Dr. Michael A. Leschziner E-mail: [email protected] Department of Engineering Queen Mary & Westfield College (QMW) University of London Mile End Road London E14NS U.K. E-mail: [email protected] Preface The survival of the Aeronautical Industries of Europe in the highly competitive World Aviation Market is strongly dependent on such factors as time-to-market of a new or derivative aircraft and on its manufacturing costs but also on the achievement of a competitive technological advantage by which an increased market share can be gained. Recognizing this, cooperative research is continuously encouraged and co-financed by the European Union in order to strengthen the scientific and technological base of the Aeronautical Industries thus providing - among others - the technological edge needed for survival. Corresponding targets of research within Area 3, Technologies for Transport Means, and here in particular Area 3A, Aeronautics Technologies, of the Industrial and Materials Technologies Program ( Brite -EuRam III, 1994 - 1998) have been identified to be aircraft efficiency, cost effectiveness and environmental impact. Concerning aircraft efficiency - relevant to the present research - a reduction in aircraft drag of 10%, a reduction in aircraft fuel consumption of 30%, and a reduction in airframe, engine and system weight of 20% are envisaged. Meeting these objectives has, of course, also a strong positive impact on the environment. In order to further technology, it is prudent to concentrate on the feasibility demonstration of a limited number of technologies of high economic and industrial impact. Examples of such technologies are, for instance, with regard to aircraft efficiency, the application of laminar flow and drag reduction technologies, technologies related to advanced large primary structures, and propulsion technologies. A general prerequisite for technology development is, of course, also the continuous improvement of the theoretical/numerical and experimental tools and, particularly in the case of aeronautical fluid dynamics, which is of interest here, the understanding of complex viscous compressible flow phenomena such as turbulence, transition, shock boundary layer interaction and separation. The fundamental research program described here is related to drag reduction and separation control; it is based on the following consideration: the development of the boundary layer and the interaction of the wing-upper-surface shock wave with the boundary layer essentially establish the flight performance of transonic transport aircraft at cruise as well as at high-speed off-design conditions. Consequently, employing shock and boundary layer control can be assumed to have a large potential for improving flight performance in terms of cruise drag, hence speed and/or fuel consumption, and with respect to the drag-rise and buffet boundaries. Control can also be utilized to design simpler-geometry wings, allowing to reduce weight and increase pay load, without the penalty of reduced aerodynamic performance. Based on the experience gained during the EUROSHOCK I project, where it was found that passive shock control by a VII perforated-surface/cavity arrangement generally leads to an increase or, at best, to marginal reductions in drag, the specific objective of the research performed here was to study the various aspects of active shock and boundary layer control, to develop and improve the computational and experimental tools needed to incorporate control concepts into the design of advanced transonic wings and to determine the aerodynamic merits of control up to flight Reynolds numbers, but also to assess the penalties associated with incorporating potential control methods into existing and new wing designs. The work was carried out by five research organizations, viz., Deutsches Zentrum fUr Luft- und Raumfahrt e.V. (DLR), Centro Italiano Ricerche Aerospaziali S.C.p.A. (ClRA), Instituto Nacional de Tecnica Aerospacial (INTA), Office National d'Etudes et de Recherches Aerospatiales (ONERA) and Defense Evaluation Research Agency (DERA), three universities, viz., the Universities of Cambridge and Karlsruhe and the Universita'di Napoli "Federico II", and four industrial partners, viz., Alenia Aeronautica, EADS-Airbus (Airbus-D), BAE SYSTEMS-Airbus (Airbus-UK Ltd.), and Dassault Aviation. The present book is, similarly to the EUROSHOCK I book, structured as follows: Firstly, the scientific and economical reasons leading to this investigation and the approach taken are outlined. This is followed by a comprehensive and critical account of the research and the results obtained - without going into excessive detail. Finally, the individual contributions of the partners are presented in the form of papers giving appropriate details of the fundamental, numerical and experimental research performed. The editors would like to thank all partners for their contribution to the success of EUROSHOCK II and for the effort they put into the preparation of the present book. The work was performed in a very harmonious way which is reflected in the high quality of the results. On behalf of the entire team, we would also like to thank the European Commission for its support. Finally, thanks are due to E.H. Hirschel, the general editor of the Notes on Numerical Fluid Mechanics and to the Springer Verlag for making this publication possible. September 2001 Egon Stanewsky Gottingen Jean Delery Paris Paolo de Matteis Capua John Fulker Bedford VIII Table of Contents A Synopsis of the Project EUROSHOCK II, E. Stanewsky, DLR, J. D6lery, ONERA, J. Fulker, DERA, P. de Matteis, CIRA, ......................................................................... 1 1 Introduction ... ............................ .......... ..................... ................. ........ 3 2 The EUROSHOCK II Project ........................................................... 9 3 Modeling of Active Control Phenomena (Task 1) ............................................................................................ 12 3.1 The test arrangements ..................................................................... 13 3.1.1 Two-dimensional channel-flow experiments ..................................... 13 3.1.2 Three-dimensional channel-flow Experiments .................................. 15 3.2 Numerical codes employed ................................................................ 16 3.3 Analysis of results .................................. ........................................... 17 3.3.1 The new control law of Karlsruhe University .... ........................ ........ 17 3.3.2 Active control by perforated-plate/cavity in 3D flow........................ 18 3.3.3 Hybrid control by passive/active cavity in 2D flow........................... 22 3.3.4 Cavity-ventilation control efficiency.................................................. 29 3.3.5 Control by discrete slot suction .......................................................... 31 3.3.6 Control by a contour bump in the shock region .................. ............... 35 3.4 Conclusion and future work ............................ .................... ............... 36 4 Numerical Simulation of Airfoil and Wing Flow with Control (Task 2) .............................................................................................. 38 4.1 Numerical methods ............................................................................. 38 4.1.1 Basic numerical methods .................................................................... 39 4.1.2 Control laws and control-law simulation ............................................ 41 4.1.3 Drag determination and the simulation of control by suction ............. 42 4.2 CFD capabilities and preliminary control concept assessment ........... 43 4.3 Parametric study of shock and boundary layer control concepts ........ 51 4.3.1 Active control by ventilation and suction schemes ............................. 51 4.3.1.1 Discrete slot suction ................ .......... .............................. ....... ............. 51 4.3.1.2 Cavity ventilation and hybrid control................ .................................. 56 IX 4.3.2 Active control by contour modifications (Bumps) .............................. 60 4.3.2.1 Steady flow conditions: airfoil studies ................................................ 60 4.3.2.2 Steady flow conditions: sheared-wing studies .................................... 64 4.3.2.3 Unsteady flow conditions - Buffet ............. .... ......... .......................... 65 4.3.2.4 Pn~umatic bump/distributed blowing ......... ................. ....................... 69 4.4 Evaluation of CFD codes .......... ................ .......... ............. ...... ..... ....... 70 4.5 Conclusions and future work ..... ................................... ..................... 70 5 Airfoil and Sheared-wing Experiments with and without Control (Task3) ..................................................................................................... 72 5.1 Experimental program ....................................................................... 73 5.2 DLR airfoil and sheared-wing experiments ....................................... 74 5.2.1 Wind tunnel characteristics ............................................................... 74 5.2.2 Airfoil characteristics and wind tunnel models .................................. 74 5.2.3 Experimental results for the ADIF and DA LV A-1A airfoils ............. 77 5.2.4 Experimental results for the ADIF infinitely swept wing .. ......... ........ 79 5.2.4.1 Hybrid control by passive ventilation/suction ..................................... 81 5.2.4.2 Control by bump and by bump plus suction .................... ................... 82 5.3 DERA large-scale airfoil experiments ................................................ 84 5.3.1 Wind tunnel characteristics ................................................................ 84 5.3.2 Airfoil characteristics and wind tunnel model ... ...... .................. ......... 85 5.3.3 Discussion of results .................................. .... ............ ......................... 86 5.3.3.1 Discrete suction ... .................. .............................. ...... .... .... .... ............. 86 5.3.3.2 Active and hybrid control.................... ...... .............................. ........... 87 5.4 Conclusion and future work ............................................................... 91 6 Benefits of Control Application to Aircraft Wings/Aircraft (Task 4) .............................................................................................. 93 6.1 Control assessment criteria .................... .......................... ................... 94 6.2 Control application to an A340-type HLF-wing aircraft ............. ........ 94 6.2.1 Assessment of control concepts ....................... .... ........ .............. .... ..... 94 6.2.2 Bump-control optimization studies ...................... ............................... 96 6.2.3 Hybrid laminar flow wing section and bump design ........................... 97 6.2.4 Flight mission benefits ....................................................................... 100 x