Conference Proceedings on Vortex Flow Aerodynamics

534 Pages·2010·53.14 MB·English

by  ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)

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mAGARD
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ADVISORY GROUP FOR AEROSPACE RESEARCH & DEVELOPMENT
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AGARD CONFERENCE PROCEEDINGS 494
Vortex Flow Aerodynamics
(LUA&odynamique des Ecoulements Tourbillonnaires)
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Recent Publications of
the Fluid Dynamics Panel
AGARDOGRAPHS (AG)
Experimental Techniques in the Field of Low Dersity Aerodynamics
AGARD AG-318 (E), April 1991
Techniques Expirimentales LUies i I'Akrodynamique i Basse Densiti
AGARD AG-318 (FR), April 1990
A Survey of Measurements and Measuring Techniques in Rapidly Distorted Compressible Turbulent Boundary Layers
AGARD AG-315, May 1989
Reynolds Number Effects in Transonic Flows
AGARD AG-303, December 1988
Three Dimensional Grid Generation for Complex Configurations - Recent Progress
AGARD AG-309, March 1988
REPORTS CR)
Aircraft Dyn amics at High Angles of Attack: Experiments and Modelling
"AGARD
R-?776, Special Course Notes, March 1991
Inverse Methods in Airfoil Design for Aeronautical and Turbomachinery Applications .
AGARD R-780, Special Course Notes, November 1990
Aerodynamics of Rotorcraft
AGARD R-781, Special Course Notes, November 1990
Three-Dimensional Supersonic/Hypersonic Flows Including Separation
AGARD R-764, Special Course Notes, January 1990
Advances in Cryogenic Wind Tunnel Technology
AGARD R-774, Special Course Notes, November 1989
ADVISORY REPORTS (AR)
Rotary-Balance Testing for Aircraft Dynamics
AGARD AR-265, Report of WG 11, December 1990
Calculation of 3D Separated Turbulent Flows in Boundary Layer Limit t
AGARD AR-255, Report of WGI 0, May 1990
Adaptive Wind Tunnel Walls: Technology and Applications
AGARD AR-269, Report of WG12, April 1990
Drag Prediction and Analysis from Computational Fluid D)namics: State of the Art
AGARD AR-256, Technical Status Review, Jne 1989
CONFERENCE PROCEEDINGS (CP)
Vortex Flow Aerodynamics
AGARD CP-494, July 1991
"p
(cid:127) (cid:127)Missile Aerodynamics
AGARD CP-493, April 1990
Aexoeynamics of Combat Aircraft Controls and of Ground Effects
AGARD CP465, October 1989
Computational Methods for Aerodynamic Design (Inverse) and Optimization o
AGARDCP-463,April 1989
S, , _ Applications of Mesh Generation to Complex 3-D Configurations " . -
'- "(cid:127)GARD J-464, April 1989...:
Fluid Dynamics of Three-Dimensional Turbulent Shear Flows and Transition
AGARD CP-438, October 1988
Validation of Computational Fluid Dynamics
AGARD CP-437. May 1988
Aerodynamic Data Accuracy and Quality. Requirements and Capjabilities in Wind Tunnel Testing
AGARD CP-429. October 1987
Aerodynamics of Hypersonic Lifting Vehicles
AGARD P-428,A pril 1987
Aerodynamic and Related Hydrodynamic Studies Using Water Facilities
AGARD CP-41 3, October 1986
Applications of Computational Fluid Dynamics in Aeronautics
AGARD CP-4 12. April 1986
Store Airframe Aerodynamics
AGARD CP* 389, October 1985
Unsteady Aerodynamics - Fundamentals and Applications to Aircraft Dynamics
AGARD CP-386. May 1985
Aerodynamics and Acoustics of Propellers
AGARD CP-366. October 1984
Improvement of Aerodynamic Performance through Boundary Layer Control and High Lift Systems
AGARD CP-365, May 1984
Wind Tunnels and Testing Techniques
AGARD CP-348, September 1983
Aerodynamics of Vortical Type Flows in Three Dimensions
AGARD CP-342. April 1983
Missile Aerodynamics
AGARD CP-336, Se!ptember 1982
Prediction of Aerodynamic Loads on Rotorcraft
AGARD CP-334. May 1982
Wall Interference in Wind Tunnels
AGARD CP-335. May 1982
Fluid Dynamics of Jets with Applications to V/STOL
AGARD CP-308, November 1981
Aerodynamics of Power Plant Installation
AGARD CP-301, May 1981
Computation of Viscous-Inviscid Interactions
AGARD CP-291, October 1980
* Subsonic/Transonic Configuration Aerodynamics
AGARD CP-285, May 1980
Turbulent Boundary Layers Experiments, Theory and Modelling
AGARD CP-271, September 1979
j Aerodynamic Characteristics of Controls
AGARD CP-262, May 1979
High Angle of Attack Aerodynamics
AGARD CP-247. October 1978
Stability Parameters
-Dynamic
AGARD CP-235, May 1978
Unsteady Aerodynamics
VAGARD CP-227, September 1977
Laminar-Turbulent Transition
AGARD CtP-224, May 1977 :
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t, Foreword
Separation-induced vortex flows are an important part of the design and off-design performance of conventional fighter
aircraft, and new or unconventional advanced fighwr designs, missiles, and space plane concepts. A better understanding is
needed in order to predict and control these vortex flows throughout the flight envelope at subsonic, transonic. and supersonic
speeds, and especially during high lift operations for take-offs, landings, and sustained and instantaneous maneuvers.
The principal emphasis of the Symposium was on the understanding and prediction of vortex flows and their effects on vehicle
performance, stability, control, and structural design loads. Topics of interest included vortex development and burst, modeling
and validation of the full range of analytical method%, slender-body vortex flows at high arigles-ot-attack. vortex control and
management, and unsteady vortex flow effects
J.F. Campbell/A.D. Young
Co-Chairmen
41
Avant-Propos
Les dcoulements tourbillonnaires Uis au di~collement jouent un r6le important dans les performances normalisi~es et le%
performances hors normes des avions de combat conventionnels. ainsi que dans la conception des avions de combat niodernes
ivolu~s ou exp~nmentaux, des missiles et des avions spatiaux.
Une meilleure comprehension de ces ph~nomines permettrait de pr~dire et de maitriser lea dcoulements tourbillonnaires, dans
tout le domaine de vol A des vitesses. subsoniques, transsoniques et supersoniques. en particulier lors des operations de
sustentanion au d~collage, it l'aterrissage, et lors des manoeuvres soutenues et ponctuelles.
'
L'accent principal do symposium a tit mis sur la comprehension etlla pr~diction des 6coulements tourbillonnaires et leurs
effets sur lea performances, la stabilit6, Ie pilotage, et lea efforts structuraux d'itude des v~hicules a~riens. Parmi lea sujets
examines on distingue: N'volution et l'&latement des taurbillons, Ia mod~lisation et la validation de l'int~gralit6 des m~thodes
analytiques, lea 6coulcments tourbillonnaires. autour des corps effil~s aux grands angles d'attaque, le contrale et la maitnse des
tourbillons et lea effets des dcoulements tourbillonnaires instationnaires. -
J.F.Campbell/A.D.Young
P Co-Prisidents do Comit6
de Programnme
.1v'
v
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Fluid Dynamics Panel
Chairman: Dr WJ.McCroskcy Deputy Chairman: Professor It J W Slooff
Senior Staff Scientist National Aerospace Laboratory NLR
US Army Aero Flightdynamics Directorate Anthony Fokkerweg 2
Mail Stop N-258-1I 10)06 B3M Amsterdam
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PROGRAMME COMMITT'EE
Dr J.F. Campbell (Co-Chairman) Professor A.D. Young (Co-Ch,,irman)
NASA Langley Research Center 70 Gilbert Road
Transonic Aerodynamics~ Branch Cambridge, CB4 3PD
Mail Stop 301 United Kingdom
Hampton. VA 2 3665-5225
United States Ir A E2senaar
National Aerospace Laboratory NLR
Prof. R. Decuypere Anthony Fokkerweg 2
Ecole Royale Militaire 1059 CM Amsterdam
Chaire de Mi~canique Appliqui~e The Netherlands
Avenue de ]a Renaissance 30
B- 1040 Brussels. Belgium Professor A.FEdc 0. Falcao
Depart. Engenharia Mecanica
Dr KJ.Orlik-Ruckemann Instituto, Superior Tecnico
Institute for Aerospace Research 1096 Lisboa Codex
NRC. Bldg M- 10 Portugal
Montreal Road
Ottawa KI A 0116, Canada Professor J.Jimenez
Escuela Tecnica Superior de
Prof. A. Bonnet Ingenieros Aeronauticos
Department At~rodynamique Dept. de Mecanica de Fluidos
Ecole Nationale Sup~rieure de Plaza del Cardena Cisneros 3
l'Aironautique et de l'Espace 28040 Madrid. Spain
10 Avenue Edouard Belin. BP 40)32
31055 Toulouse Cedex, France Dr U.Kaynak
TUSAS
Prof, Dr Ing. K. Gersten Havacilik ye Uzay San. A S.
Institut fiir Thermo- und Fluiddynamik P.K. 18 Kavaklidere
Ruhr-Unjversitiit Bochum 06690 Ankara
Postfach 10 21 48 Turkey
D-4630 Bochum 1, Germany
Dr R.G.Bradley
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Dipartimento di Ingegneria Mail Zone 2888
Aeronautica e Spaziale General Dynamics, Fort Worth Div.
Politeenico di Torino P.O. Box 748
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Contents
Page
Recent Publications of the Fluid Dynamics Panel i
Foreword/Avant-Propos v
Fluid Dynamics Panel vi
Reference
SESSION I - VORTEX COMPUTATIONAL TECHNIQUES - I
Chairman: A.B onnet
Modeling and Numerical Simulation of Vortex Flow in Aerodynamics 1
by H.W.M.Hoeijmakers
Comparison of Solution of Various Euler Solvers and One Navier-Stokes Solver 2
for the Flow about a Sharp-Edged Cropped Delta Wing
by B.R. Williams, W.Kordulla, M.Borsi and H.W M Hoeijmakers
Vortical Flow Simulation by Using Structured and Unstructured Grids 3
by M. Borsi ct al.
Analysis of Results of an Euler-Equation Method Applied to Leading-Edge Vortex Flow 4
by J.1. van den Berg, H.W.M.Hoeijmakers and J.MJ.W. Jacobs
Experimental and Numerical Investigation of the Vortex Flow over a Delta Wing 5
at Transonic Speed
by E.M. Houtman and W.J. Bannink
SESSION I - VORTEX COMPUTATIONAL TECHNIQUES - 11
Chairman: R.G. Bradley
Sby.J.RMevi.eLw uofc Vkonrteixn Cgomputational Techniques 6
On the Simulation of Compressible Turbulent Flows past Delta Wing, Delta Wing-Body 7
and Delta Wing-Canard
by A.Hilgenstock and H.Vollmers t
Calculation of Hypersonic Leeside Vortices over Blunt Delta Wings 8
by A.Rizzi, E M.Murman, P.Eliasson and K.-M.Lee
On the Footprints of Three-Dimensional Separated Vortex Flows around Blunt Bodies 9
by U.1Dallmann. A.Hilgenstock, S.Riedelbauch, B.Schulte-Werning and H.Volimers
Laminar-Flow Secondary Separation on a Slender Wing 10
by K. Kirkk6pri and N. Riley
Nonequilibrium Turbulence Modeling Effects on Transonic Vortical Flows about Delta Wings 11
by U. Kaynak, E.Tu, M. Dindar and R. Barlas
"SESSION
III MEASUREMeNTS AND VISUALIZATION
.-
Chairman: M.Onorato
Review of Aircraft Dynamic Loads Due to Flow Separation 12
by D.G.Mabey
In-Flight Flow Visualization and Pressure Measurements at Low Speeds on the NASA F- 18 13
High Alpha Research Vehicle
by J.H.Del Frate, D.F.Fisher and FA.Zuniga
-KY, V_
Reference
Vortex Formation over a Close-Coupled Canard-Wing-Body Configuration 14
in Unsymmetrical Flow
by A. Bergmann, D.Hummel and H.-Chr. Oelker
An Experimental Study of the Flow over a Sharp-Edged Delta Wing at Subsonic 15
and Transonic Speeds
by A. Elsenaar and H.W.M. Hoeijmakers
Caractiristiques d'une Couche Limite en Aval d'un Tourbillon de Bord d'Attaque 16
par G.Pailhas et J.Cousteix
SESSION IV - SLENDER-BODY VORTEX FLOWS
Chairman: K.G ersten
Ecoulement Tourbillonnaire sur Fuselage de Missile Etude Expkrimentale et Modklisation 17
par P. Champigny et D. Baudin
Asymmetric Vortex Flow over Circular Cones 18
by M. Pidd and J.H.B.Smith
An Experimental Investigation of the Effect of Fineness Ratio on Lateral Force 19
on a Pointed Slender Body of Revolution
by I.R.M.Moir
SESSION V - VORTEX DEVELOPMENT AND BREAKDOWN
Chairman: A.E lsenaar
Physique des Ecoulements Tourbillonnaires 20
par J. Delery
Breaking Down the Delta Wing Vortex: The Role of Vorticity in the Breakdown Process 21
by R.C. Nelson and K D.Visser
D6termination de Critires d'Eclatement Tourbillonnaire par R6solution des Equations d'Euler 22
et de Navier-Stokes
par T.H. Le, Ph. Mege et Y. Morchoisne
Etudes Fondamentales sur I'Eclatement Tourbillonnaire et son Contr6le 23
par D.Pagan et P. Molton
Investigation of Vortex Breakdown on a Delta Wing Using Euler and Navier-Stokes Equations 24
by S. Agrawal, R.M. Barnett and B.A. Robinson
SESSION VI - VORTEX CONTROL
Chairman: A.D.Young
Vortex Control - Further Encounters 25 J
byD.M.Rao
On Aircraft Wake Properties and some Methods for Stimulating Decay and Breakdown 26
of Tip Vortices
by R. Staufenbiel and T. Vitting
Control of Forebody Vortices by Suction at the Nose of the RAE High Incidence Research Model 27
by AJ. Ross, E.BJefferies and G.F. Edwards
An Experimental Investigation of Vortex Flaps on a Canard Combat-Aircraft Configuration 28
byD.A.Lovell
f
viii
(cid:127);-Z(cid:127) --
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"~" ~.~-. ~~~~~~.~~"(cid:127) tl " - , l I I I I l (cid:127) III II I I I .. . . . . . .. .
Reference
SESSION VII - UNSTEADY EFFECTS
Chairman: K.J.Olik.R1fckemann
Steady and Unsteady Aerodynamics of a Pitching Straked Wing Model at High Angles of Attack 29
by A.M. Cunningham Jr and R.G. den Boer
Some Characteristics and Effects of the F/A- 18 LEX Vortices 30
by D.B rown, B.H.K. Lee and F.C. Tang
Multiple Roll Attractors of a Delta Wing at High Incidence 31
by E S. Hanff and L.E.Ericsson
Numerical Simulation of Vortex Street-Edge Interaction 32
by M.O. Kaya, C.R. Kaykayoglu, K.C Bayar and J M.R. Graham
Numerical Simulation of Vortex Flows past Impulsively Started Wings 33
by A.B aron, M.Boffadossi and S.De Ponte
Round Tahle Discussion RTD
-V
MI
:'Ph
MODE~VLOINRGT EAXN FDL NOUWM IENR AIECRAOLD SYINMAUMIAICTSION OF
by
H.W.M.Hoeljmakers,
National Aerospace Laboratory NLR
Anthony Fokkerweg 2,1059 CM Amsterdam
The Netherlands
SUMMARY Other separations such as "closed" type of separa-
review is presented of mathematical models of tions involve regions with recirculating flow.
This type of vortex flow is largely dominated by
different level of approximation for and their ap- viscous effects, often occurs at off-design condi-
plication to the numerical simulation of vortical tions and has associated with it a usually un-
type of flows occurring in subsonic and transonic steady and not-well-ordered vortical flow struc-
aircraft aerodynamics. The paper covers computa- ture.The latter type of vortical flow is outside
tional methods for predicting the downstream de- the scope of the present paper, which is primarily
velopment of vortex wakes as well as methods for concerned with controllable and exploitable types
simulating the detailed characteristics of config- of vortex flow.
urations with leading-edge or body vortices. The
emphasis is on the latter, strong-interaction, Two types of vortex flow may be distinguished,
type of vortical flows, vortex flow where there is a weak and vortex flow
Promising new developments of the methods used at where there is a stron interaction between the
present are discussed in some detail. The possi- vortical flow structures and the flow over the
bilities, limitations and prospects of improvement surface of the configuration.
of the methods are indicated and results of dif-
ferent methods are discussed,
Also considered are some more fundamental aspects FLAP
of the numerical simulation such as separation at SINGLE-BRANCHED
4smooshatrhp and round leading edges, separation at a VORTEX CORE
part of the surface., the structure of the U
leading-edge vortex and the merging of two vor-
tices.
1. INTRODUCTION SMER
In aircraft aerodynamics flows involving free DOUBLE-a
shear (vortex) layers and vortex cores, generally VORTE- CRE
termed vortex flows, play an important role VORTEX CORE
(Kichemann, Ref. 1). At the high Reynolds numbers Fig. 1 Vortex wake; Weak-interaction vortex flow
pertinent to aircraft aerodynamics free shear lay-
aer form whenever the flow encounters a sharp The flow in the wake downstream of the trailing
edge. The properties of the (thin) shear layer are edge of a transport type of wing is usually a
determined by the conditions that at the edge (a weak-interaction type of vortex flow. In this caser
geometrical singularity) the velocity remains fi- the vorticity vector is in a direction approximp-
nLte and that vorticity is convected away from it, rely perpendicular to the separation line, i.e. in
i.e. the Kutta condition. It should be-realized this case the trailing edge (Fig. 1). This means
that in the three-dimensional high-Reynolds-number that the region with vortical flow is not in the
flow of interest here the vorticity contents of close proximity of the configuration and that the
the shear layer is primarily determined by the influence of the vorticity on the velocity and
shear of the v:elocity vector (i.e. magnitude of pressure distribution on the surface of the con-
the disconcinuity in its direction) across the figuration-will be small. For weak-interaction
separation line, not by the vorticity within the vortex-flow the lift increases approximately lin-
viscoAs layers meeting at the separation line early with incidence, at least until viscous flow
A(Hwaiyr scfrhoeml, thRee f.e dg2e). the shear layer usually rolls effects become significant.
up into one or more vortex cores which remain em- Strong-interaction-vortex flow can occur when the
bedded within the shear layer and are continuously flow separates at the side edge of a low-aspect.
fed with vorticity from the shear layer, Sooner or ratio wing of low sweep or'at the highly swept
later most of the vorticity generated at the edge leading edge of a slender wing (Fig. 2) and also
will be concentrated in these regions with dis- when the flow separates froi the smooth surface of
Sstructure tsriisbtuetnetd. vios rtoicftietyn . wTehlel -orredseurletdin, g svteoardtyic aanld fploewr- acthatesede s f obrotehdbeyo vdoyof roati fcm iati ysfs iigvlehe Zccteoor rn afiiisgr cuarrapatpfitro onxo.i rmitIahnte e ltyhe elopsneag-r-al-
t te lel to the separation line. A strong interaction
Ona n aircraft configsration, the flow may separate alsotakes place when-the vortex wake of one com-
before a sharp edge is reached, i.e. at a smooth ponent of the configurati6h closely approaches
portion of~the surface. In contrast, to the separa- other components of:the aircraft. pExamaeres the
tion at a sharp edge the locationof. the smooth- interaction of-the wake of the wing with th" flow
surface separation depends on Mach number, mici- abo-t the tail surfa-es, the flow-abou. (cid:127) "close-
dance, Reynolds number,, state of the boundary, lay- coupled* canard~wing configuritionaid the flow
or, etc. and is nbt knowna priori-. In thres-di- aboutia'trake~wing;'configuration. Inthe case of
mensional floathis'type of separation ( spi)a.- strong inteiactibi-the i6tational flow'region(s)r
cifically the. so~called "(cid:127)open" type- of, separation) are close-to the surface of- th -configur~tiii and-
° (cid:127) : md"i~a"dy~ er~neifs ~flulo owlowt oAa-Rtn -s raut cnn touutchrreee,r , wAehlilh-d eIi ftianeee ldf ainssnd nsoot etabvvd eyr-yv ore-- ootefintoeearnh-iil'tri enenmeear.p"-xTittk(cid:127)oh fehien 6ltaoha cea ln esuarr fapcieb xVimeloitcyi-tyo th&en d'iioepeasisau-re ii'
pdidant on Reynolds numberdstribuion. d h overall cacteristics of
P,w-ir tially funded through the Netherlands Agency for Aerospace Prgram
"(NIVR)
for the Netherlands Ministry of Defence
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