Summary of WakeNet2-Europe WG7 Workshop: “Principles of ... · Don Durston, NASA AmesDon Durston,...

Summary of WakeNet2-Europe WG7 Workshop:“Principles of Wake Vortex Alleviation Devices”

Summary of WakeNet2-Europe WG7 Workshop:“Principles of Wake Vortex Alleviation Devices”

Workshop held at ONERA, Toulouse, FranceFebruary 9-10, 2005

Followed by ONERA Joint Project Meeting:“Wake Vortex Dynamics” February 11, 2005

Workshop held at ONERA, Toulouse, FranceFebruary 9-10, 2005

Followed by ONERA Joint Project Meeting:“Wake Vortex Dynamics” February 11, 2005

Briefing for WakeNet USA meetingMarch 16–17, 2005, Boca Raton, Florida

Don Durston, NASA Ames Research Center

Briefing for WakeNet USA meetingMarch 16–17, 2005, Boca Raton, Florida

Don Durston, NASA Ames Research Center

WakeNet2-Europe

Don Durston, NASA AmesDon Durston, NASA Ames 22

WakeNet2-Europe

OutlineOutline

• Overview of ONERA and WakeNet2-Europe• Meeting Programs• Summary Table of Briefings• Excerpts from Briefings• Summaries from Abstracts and Notes• Minix Wing Tip• Overall Impressions, Conclusions

• Overview of ONERA and WakeNet2-Europe• Meeting Programs• Summary Table of Briefings• Excerpts from Briefings• Summaries from Abstracts and Notes• Minix Wing Tip• Overall Impressions, Conclusions


WakeNet2-Europe

ONERAOffice National d’Etudes et de Recherches Aérospatiales(National Office of Aerospace Studies and Research)

ONERAOffice National d’Etudes et de Recherches Aérospatiales(National Office of Aerospace Studies and Research)

• ONERA has 8 sitesaround France

• The February 2005wake vortex meetingswere held in Toulouse

• ONERA has 8 sitesaround France

• The February 2005wake vortex meetingswere held in Toulouse

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WakeNet2-Europe





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WakeNet2-EuropeONERA Workshop Program, Day 1ONERA Workshop Program, Day 1

Wednesday, February 9, 2005

from 9.00 # Welcoming Coffee, Registration 10.00 Welcome

M. de Gliniasty, General Scientific Director of ONERA, E. Coustols (local organiser)

10.15 Š 10.30 Introduction to the workshop A. Elsenaar, coordinator WakeNet2-Europe, Workshop Chairman

10.30 Š 11.20 An overview of European Projects on Wake Vortices E. Coustols, ONERA, Toulouse, Workshop Co-Chairman

Session 1: Near-wake dynamics 11.20 Š 11.55 1 Interaction of two unequal non-uniform vortices, R.R. Trieling, G.J.F. van Heijst, T.U. Eindhoven, The

Netherlands & O.U. Velasco Fuentes, CICESE, Ensenada, Mexico. 11.55 Š 12.30 2 Investigation on vortex/engine-jet interaction in the near-wake of a swept wing with different engine positions,

G. Huppertz & W. Schroeder, RWTH Aachen, Germany.

12.30 Š 14.00 Lunch

14.00 Š 14.50 3 Invited paper: Dynamics of trailing vortices in the extended near-wake: short-wave instability and merging, T. Leweke, IRPHE, Marseille.

14.50 Š 15.25 4 Numerical simulation of two co-rotating vortices in the extended near-field of aircraft wake, L. Nybelen, H. Moet, R. Paoli & G. Chevalier, CERFACS, Toulouse, France.

15.25 Š 16.00 5 Effect of span loading modification on the near- to mid-wake flow field, F. Moens, J-B. Dor, L. Jacquin,P. Molton & E. Coustols, ONERA, Ch‰tillon, Chalais-Meudon & Toulouse, France.

16.00 Š 16.30 Coffee/Tea

Session 2: Far Wake Dynamics 16.30 Š 17.05 6 Wake Vortex Alleviation Flow Field Studies, D. Durston, NASA Ames, USA. 17.05 Š 17.40 7 LES of instabilities, vortex reconnection and global decay of counter-rotating four-vortex systems,

L. Dufresne, G. Winckelmans & R. Capart, UCL Louvain la Neuve, Belgium.

17.45 Closing of first day, evening program

U.S. papers highlighted in yellow


WakeNet2-Europe

Thursday, February 10, 2005

09.00 Š 09.20 8 Investigation on 4 Vortex system with respect to vortex alleviation and consideration of end-effect,

H. Vollmers & F. Bao, DLR, G�ttingen, Germany. [Heinrich Vollmers passed away the week prior to the workshop] Commemorating our colleague Heinrich Vollmers by his work on wake vortices, Thomas Gerz, DLR, Germany.

09.20 Š 10.10 9 Invited paper: Far-field Wake Vortices: Stability and Turbulence, L. Jacquin ONERA, Chalais-Meudon, France.

10.10 Š 10.45 10 Wake Vortex decay characteristics and robustness of alleviating devices in atmospheric environments, T. Gerz & R. Baumann, DLR Oberpfaffenhofen, Germany.

10.45 Š 11.00 Coffee

Session 3: Control 11.00 Š 11.35 11 Wake Vortex alleviation by means of passive vortex devices,

C. Bellastrada & C. Breitsamter, TUM-FLM, M�nchen, Germany. 11.35 Š 12.10 12 Assessment of wake-vortex-control strategies, J. Crouch, Boeing Commercial Airplanes, Seattle, USA. 12.10 Š 12.45 13 State of the current research on wake vortex alleviation,

G. Voss, DLR, Braunschweig, Germany & E. Stumpf, DLR, Koeln, Germany.

12.40 Š 14.00 Lunch

14.00 Š 14.50 14 Invited paper: Passive Wake Vortex Alleviation, O. Savas, University of California, Berkeley, USA.

14.50 Š 15.25 15 Boundary layer control: an effective and feasible method for wake management, D. Greenblatt & A. E. Washburn, NASA Langley, USA.

15.25 Š 16.00 16 Effect of continuous and pulsed blowing on the near- to mid-wake flow field generated behind a simple model and a generic aircraft-type model, E. Coustols, J-B. Dor, L. Jacquin, P. Molton, F. Moens & G. Pailhas, ONERA, Ch‰tillon, Chalais-Meudon & Toulouse, France.

16.00 Š 16.30 Coffee/Tea

16.30 Š 17.00 17 Technical Evaluation F. Laporte, Airbus Deutschland, Bremen, Germany

17.00 Š 17.30 18 Discussions, chaired by Bram Elsenaar

17.30 Š 18.15 Visit of T2 transonic wind tunnel & THALES water tunnel

ONERA Workshop Program, Day 2ONERA Workshop Program, Day 2

U.S. papers highlighted in yellow


WakeNet2-EuropeONERA Joint Project Meeting ProgramONERA Joint Project Meeting Program

Friday, February 11, 2005

09.00 Welcome

P. Kuentzman, Deputy, General Scientific Director of ONERA, X. de Saint Victor (local organiser)

09.10 Š 09.50 19 The ONERA Joint Project X. de Saint Victor, Project Leader, ONERA, Toulouse, France.

09.50 Š 10.20 Coffee

10.20 Š 11.00 20 Wake vortex characterization by Lidar technics: catapult and field trials, A. Dolfi-Bouteyre & J-P. Cariou, ONERA, Palaiseau, France.

11.00 Š 11.40 21 Instabilities developing in a wing tip counter rotating vortex pair: experimental evidence and control, G. Pailhas, ONERA, Toulouse, France.

11.40 Š 12.20 22 Numerical simulation of exhaust dispersion and contrail formation in the near-field of an aircraft wake, F. Garnier, ONERA, Ch‰tillon, France, R. Paoli, CERFACS, France & P. Mirabel, CNRS Strasbourg, France.

12.20 Š 14.00 Lunch

14.00 Š 14.40 23 Numerical simulations of wake vortices: i) behind an aircraft-type model, ii) in-ground effect, and, iii) jet-wake interaction, O. Labbˇ & X. de Saint Victor, ONERA, Ch‰tillon, Toulouse, France.

14.40 Š 15.20 24 Fundamental on vortices: status and perspectives, L. Jacquin, ONERA, Chalais-Meudon, France.

15.20 Š 15.45 Discussions

15.45 Closing of the meeting

ONERAName First Name Organisation e-mail address Feb. 9 Feb. 10 Feb. 11Welcome by ONERA General Scientific Directorde GLINIASTY Michel ONERA/DSG [email protected] XKUENTZMANN Paul ONERA/DSG/A [email protected] XBOUTIER Alain ONERA/DSG/A [email protected] X

Keynote SpeakersJACQUIN Laurent ONERA [email protected] X X XLEWEKE Thomas IRPHE [email protected] X X XSAVAS Omer U.C. Berkeley [email protected] X X X

Speakers BELLASTRADA Claudio TU Munchen [email protected] X X xCARIOU Jean-Pierre ONERA/DOTA [email protected] XCOUSTOLS Eric ONERA/DMAE [email protected] X X xCROUCH Jeffrey D. Boeing Company [email protected] X Xde SAINT VICTOR Xavier ONERA/DMAE [email protected] x x XDUFRESNE Louis UCL Louvain [email protected] X XDURSTON Donald A. NASA Ames [email protected] X X xGARNIER Francois ONERA/DMPH [email protected] x x XGERZ Thomas DLR Oberpf. [email protected] X X xHUPPERTZ Guido RWTH Aachen [email protected] X X xMOENS Frédéric ONERA/DAAP [email protected] X X xNYBELEN Laurent CERFACS [email protected] X X xPAILHAS Guy ONERA/DMAE [email protected] x x XTRIELING Ruben TU Eindhoven [email protected] X X xVOSS Guido DLR Brauns. [email protected] X X xWASHBURN Anthony NASA Langley [email protected] X X x

Attendance onlyde BRUIN Anton NLR Marknesse [email protected] x x xBRULHART David Switzerland [email protected] x x xCHEVALIER Guilhem CERFACS [email protected] x x xELSENAAR Abraham Past-NLR [email protected] x x xHINSINGER Robert AIRBUS SAS [email protected] x xHUGUES Christian MINIX [email protected] x x xKHORRAMI Mehdi R. NASA Langley [email protected] x x xLAPORTE Florent AIRBUS-D [email protected] x x xMOLTON Pascal ONERA/DAFE [email protected] x x xPAOLI Roberto CERFACS [email protected] x x xPARCELIER Benoît ENSICA [email protected] x x xRICO CUSI Fernando J. NASA Langley [email protected] x x xRODIER Caroline ENSICA [email protected] x x xROKHSAZ Kamran Wichita State Univ [email protected] x x xROY Clément IRPHE [email protected] x x xRUDNIK Ralf DLR Brauns. [email protected] x x xSCHMIDT Katrin AIRBUS-D [email protected] x x xSCHRAUF Geza AIRBUS-D [email protected] x x xTHOMAS Olivier ONERA/DAFE [email protected] x x xWINCKELMANS Grégoire UCL Louvain [email protected] x x

Total Participation 39 37 38

WG7 WorkshopAttendance

WN2E WG7 Workshop List of Participants

ONERAMeetingAttendees

ONERAMeetingAttendees

U.S. attendeeshighlighted in yellow

Summary Table of BriefingsSummary Table of Briefings

NoNoCompCompMid-fieldMid-fieldCounterCounter44PassivePassiveGenericGeneric77

NoNoExpExpFar-fieldFar-fieldCounterCounter44PassivePassiveGenericGeneric66

NoNoExpExpMid-fieldMid-fieldBothBothMultipleMultiplePassivePassiveRealisticRealistic55

NoNoCompCompNear-fieldNear-fieldCo-rotatingCo-rotating22PassivePassiveGenericGeneric44

NoNoExp, CompExp, CompMid-fieldMid-fieldCo-rotatingCo-rotating22PassivePassiveGenericGeneric33

YesYesExpExpNear-fieldNear-fieldCo-rotatingCo-rotating22PassivePassiveRealisticRealistic22

NoNoExp, CompExp, CompMid-fieldMid-fieldCo-rotatingCo-rotating22PassivePassiveGenericGeneric11

YesYesExp, CompExp, CompMid-fieldMid-fieldBothBothMultipleMultiplePassivePassiveBothBoth2323

YesYesComp,Comp, FlightFlight??BothBothMultipleMultiplePassivePassiveRealisticRealistic1010

NoNoExpExpNear-fieldNear-fieldBothBothMultipleMultiplePassivePassiveRealisticRealistic1111

22

22

MultipleMultiple

MultipleMultiple

MultipleMultiple

MultipleMultiple

44

MultipleMultiple

MultipleMultiple

2, 4, or2, 4, orMultipleMultiple

No. ofNo. ofVorticesVortices

GenericGeneric

GenericGeneric

RealisticRealistic

BothBoth

BothBoth

GenericGeneric

GenericGeneric

RealisticRealistic

BothBoth

GenericGenericoror

RealisticRealistic

Config.Config.

Yes or NoYes or NoComputational,Computational,ExperimentalExperimental

(ground), or Flight(ground), or Flight

Near-, Mid- orNear-, Mid- orFar-fieldFar-field

Co- orCo- orCounterCounterRotatingRotating

PassivePassiveor Activeor Active##

YesYesCompCompNear-fieldNear-fieldCounterCounterPassivePassive2222

NoNoExpExpNear-fieldNear-fieldCounterCounterPassivePassive2121

NoNoExp, FlightExp, FlightFar-fieldFar-fieldBothBothPassivePassive2020

YesYesExp, CompExp, CompFar-fieldFar-fieldBothBothBothBoth1919

NoNoExpExpMid-fieldMid-fieldBothBothBothBoth1616

NoNoExpExpNear-fieldNear-fieldBothBothActiveActive1515

NoNoExp, CompExp, CompFar-fieldFar-fieldCounterCounterPassivePassive1414

NoNoExp, CompExp, CompFar-fieldFar-fieldBothBothBothBoth1313

NoNoExp,Comp,Exp,Comp,SimSimFar-fieldFar-fieldBothBothBothBoth1212

Jet /VortexJet /VortexInteractionsInteractionsData TypeData TypeFurthest DistanceFurthest Distance

DownstreamDownstreamVortexVortex

RotationsRotationsType ofType of

AlleviationAlleviationBriefingBriefing


WakeNet2-Europe

Notes for Summary Table of BriefingsNotes for Summary Table of Briefings

•• Active alleviation implies externally-induced instabilities; all othersActive alleviation implies externally-induced instabilities; all otherspassivepassive

•• Generic configuration implies basic or fundamental research; realisticGeneric configuration implies basic or fundamental research; realisticconfiguration implies more applied research with at least some elementsconfiguration implies more applied research with at least some elementsof practical airplane configuration if not allof practical airplane configuration if not all

•• Near-field (Near-field (““extendedextended near-fieldnear-field””) to 10 spans; mid-field to 100 spans,) to 10 spans; mid-field to 100 spans,far-field beyond 100 spansfar-field beyond 100 spans

•• Jet implies engine efflux, as opposed to blowing out of various airframeJet implies engine efflux, as opposed to blowing out of various airframecomponentscomponents


WakeNet2-EuropeLaurent Jacquin, ONERA:On the Dynamics of Vortices

Laurent Jacquin, ONERA:On the Dynamics of Vortices

Short-wave instabilitiesShort-wave instabilities

Status• Big progress—we learned a lot• Influence on hazard ?• Non-linear regime…be careful (saturation)

Status• Big progress—we learned a lot• Influence on hazard ?• Non-linear regime…be careful (saturation)

Long-wave instabilitiesLong-wave instabilities

Status• Big progress—we learned a lot• Seems we have the physics• Alleviation: encouraging• A challenge for CFD before concluding• A challenge for applied aerodynamics and

flight test people

Status• Big progress—we learned a lot• Seems we have the physics• Alleviation: encouraging• A challenge for CFD before concluding• A challenge for applied aerodynamics and

flight test people


WakeNet2-EuropeLaurent Jacquin, ONERA:On the Dynamics of Vortices

Laurent Jacquin, ONERA:On the Dynamics of Vortices

Axial flowAxial flow

Status• In progress…• On-going refinements: new fundamental

finding expected• Importance for alleviation: to be demonstrated

Status• In progress…• On-going refinements: new fundamental

finding expected• Importance for alleviation: to be demonstrated

Jet/vortex mixingJet/vortex mixing

Status• A vortex may be destabilized by density

variations if the core is heavier thansurrounding fluid

• A parametric study is in progress• Either a strong density contrast (R > 0.3), or a

strong concentration of the density variation(b/a < 0.5) is required: weak potential for WV

Status• A vortex may be destabilized by density

variations if the core is heavier thansurrounding fluid

• A parametric study is in progress• Either a strong density contrast (R > 0.3), or a

strong concentration of the density variation(b/a < 0.5) is required: weak potential for WV


WakeNet2-Europe

Validation of CodesValidation of CodesSequential Axial Vorticity Simulation of Vortex Wake of DLR-F11 ModelSequential Axial Vorticity Simulation of Vortex Wake of DLR-F11 Model

TAU (TAU (EulerEuler)) x/b = 0.5 x/b = 0.5

2D-2D-EuLagEuLag (MILES) (MILES) x/b = 6 x/b = 6

ExperimentExperiment SimulationSimulation

Guido Voß, Eike Stumpf, DLR:Wake Alleviation by Configurative Modifications



WakeNet2-EuropeGuido Voß, Eike Stumpf, DLR:Wake Alleviation by Configurative Modifications


DLR-ALVAST model

Near-field Simulation of Configurative MethodWake vortex development depends on engine exhaustNear-field Simulation of Configurative MethodWake vortex development depends on engine exhaust

NoengineNoengine With engineWith engine


WakeNet2-Europe

iso-vorticity surface ⏐ω⏐ = 5% ωini-max

t* = 0...1.76

Numerical Strategy for Wake Vortex Prediction Temporal Development of 4-Vortex System



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WakeNet2-Europe

Flap Tip ModificationsFlap Tip ModificationsDLR-F11 in Take-Off ConfigurationDLR-F11 in Take-Off Configuration

Flaplet

SquareFlaplet

TurbulenceGenerator



Flaplet

SquareFlaplet

TurbulenceGenerator

Baseline

PT LOSS0.030

0.020

0.010

0

5-hole5-holeprobeprobe

surveyssurveys

x/b = 0.5x/b = 0.5


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Vortex devices testedVortex devices testedon 1.3m-span LTA-E4on 1.3m-span LTA-E4half-modelhalf-model

TriangularFlap Plate

Double-Swept Plate

Cylinder

Claudio Bellastrada, Christian Breitsamter, TUM-FLM:Wake Vortex Alleviation by Means of Passive Vortex Devices


Hot-wireHot-wireprobeprobe

surveys at surveys at x*x*= 5.6= 5.6

0.00

0.05

0.10

0.15

0.20

0.25M

ax In

duce

d R

M

Baseline Flap Plate Double SweptPlate

Cylinder


WakeNet2-EuropeClaudio Bellastrada, Christian Breitsamter, TUM-FLM:Wake Vortex Alleviation by Means of Passive Vortex Devices


WTV = Wing Tip VortexWTV = Wing Tip Vortex

OFV = Outbd Flap VortexOFV = Outbd Flap Vortex

Differential flapDifferential flapsetting (DFS) of 8setting (DFS) of 8°°/26/26°°

shownshown


WakeNet2-EuropeThomas Gerz & Robert Baumann, DLR:Wake vortex decay characteristics and robustness ofalleviating devices in atmospheric environments

Thomas Gerz & Robert Baumann, DLRThomas Gerz & Robert Baumann, DLR::Wake vortex decay characteristics and robustness ofWake vortex decay characteristics and robustness ofalleviating devices in atmospheric environmentsalleviating devices in atmospheric environments

110 m

L3 L2 L1

0 234 814

L1: pulsed lidar, DLRL2: cw lidar, DLRL3: cw lidar, ONERA

C-Wake and AWIATOR campaigns in C-Wake and AWIATOR campaigns in Tarbes Tarbes 2002/032002/03LIDAR set-up for LIDAR set-up for WakeTOUL WakeTOUL and Flight Test 1and Flight Test 1


WakeNet2-Europe

Gerz & Baumann:Wake vortex decay…

Gerz & BaumannGerz & Baumann::Wake vortex decay…Wake vortex decay…

Lidar Lidar measurements of aircraftmeasurements of aircraftwake vortices in wake vortices in TarbesTarbes

Influence of Influence of turbulenceturbulence on vortex on vortexdecay, circulation vs. timedecay, circulation vs. time

Wake-TOUL (C-Wake) 2002

FT-1 (AWIATOR) 2003


WakeNet2-EuropeThomas Gerz & Robert Baumann, DLR:Wake vortex decay characteristics and robustness ofalleviating devices in atmospheric environments

Thomas Gerz & Robert Baumann, DLRThomas Gerz & Robert Baumann, DLR::Wake vortex decay characteristics and robustness ofWake vortex decay characteristics and robustness ofalleviating devices in atmospheric environmentsalleviating devices in atmospheric environments

Lidar Lidar measurementsmeasurementsof aircraftof aircraftwake vortices inwake vortices inTarbesTarbes

Influence ofInfluence ofconfigurationconfiguration on onvortex decay,vortex decay,circulation vs. timecirculation vs. time

Normalised circulation: day 2, configuration b, 1 and 2, AWIATOR 2003Normalised circulation: day 2, configuration b, 1 and 2, AWIATOR 2003


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 1 — Interaction of two unequal non-uniform vortices, R.R. Trieling

Co-rotating, merging vortices with Gaussian vorticity distributionsNear- to mid-field computational results

• 2 — Investigation on vortex/engine-jet interaction in the near-wake of a swept wing withdifferent engine positions, G. Huppertz

Swept-wing half-model with jet engineExperimental results of engine position effects on flap-edge and wing-tip vorticesFlap-edge vortex more strongly influenced by engine position than tip vortex

• 3 — Dynamics of trailing vortices in the extended near-wake: short-wave instability andmerging, T. Leweke

Merging and elliptic instabilityRelevance to realistic aircraft wakes, strategies for vortex control

• 4 — Numerical simulation of two co-rotating vortices in the extended near-field of aircraftwake, L. Nybelen

DNS study of merging to several spans downstreamCo-rotating, symmetric vortices

• 1 — Interaction of two unequal non-uniform vortices, R.R. TrielingCo-rotating, merging vortices with Gaussian vorticity distributionsNear- to mid-field computational results

• 2 — Investigation on vortex/engine-jet interaction in the near-wake of a swept wing withdifferent engine positions, G. Huppertz

Swept-wing half-model with jet engineExperimental results of engine position effects on flap-edge and wing-tip vorticesFlap-edge vortex more strongly influenced by engine position than tip vortex

• 3 — Dynamics of trailing vortices in the extended near-wake: short-wave instability andmerging, T. Leweke

Merging and elliptic instabilityRelevance to realistic aircraft wakes, strategies for vortex control

• 4 — Numerical simulation of two co-rotating vortices in the extended near-field of aircraftwake, L. Nybelen

DNS study of merging to several spans downstreamCo-rotating, symmetric vortices


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Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 5 — Effect of span loading modification on the near- to mid-wake flow field, F. Moens

Review of ONERA’s two strategies:lvv - low vorticity vortex: increase vorticity diffusion in near-field, or produce larger, weaker, or more turbulentvorticesqdv - quickly decaying vortex: long-wave instabilities to promote premature collapse

Passive concepts studied, using wing span-loading modificationsTested in ONERA F2 subsonic WT and in B10 catapult facilityResult: span loading modifications did alter vortex trajectories in mid-field (~60 spans)

• 6 — Wake Vortex Alleviation Flow Field Studies, D. DurstonPassive, 4-vortex system from generic wing-tail configurationPIV and flow viz studies in 60m tow tankVortex merging in 60-75 spans, primary vortices significantly reduced in strengthAssessment of high tail downloads and excessive longitudinal stability shows difficulty of thisconcept being practical

• 7 — LES of instabilities, vortex reconnection and global decay of counter-rotating four-vortex systems, L. Dufresne

Good CFD visualization of vortex interactions & decay for 4-vortex systemsBut, no mention of practical way to achieve such high vortex strength ratios

• 5 — Effect of span loading modification on the near- to mid-wake flow field, F. MoensReview of ONERA’s two strategies:

lvv - low vorticity vortex: increase vorticity diffusion in near-field, or produce larger, weaker, or more turbulentvorticesqdv - quickly decaying vortex: long-wave instabilities to promote premature collapse

Passive concepts studied, using wing span-loading modificationsTested in ONERA F2 subsonic WT and in B10 catapult facilityResult: span loading modifications did alter vortex trajectories in mid-field (~60 spans)

• 6 — Wake Vortex Alleviation Flow Field Studies, D. DurstonPassive, 4-vortex system from generic wing-tail configurationPIV and flow viz studies in 60m tow tankVortex merging in 60-75 spans, primary vortices significantly reduced in strengthAssessment of high tail downloads and excessive longitudinal stability shows difficulty of thisconcept being practical

• 7 — LES of instabilities, vortex reconnection and global decay of counter-rotating four-vortex systems, L. Dufresne

Good CFD visualization of vortex interactions & decay for 4-vortex systemsBut, no mention of practical way to achieve such high vortex strength ratios


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• (presentation cancelled) Investigation on 4 Vortex system with respect to vortex alleviation

and consideration of end-effect, H. Vollmers4-vortex counter-rotating systems using inbd flap edge and/or h. tail for counter-sign vorticesNo mention of practicality of such systems

• 8 — Commemorating our colleague Heinrich Vollmers by his work on wake vortices,Thomas Gerz (abstract not provided; presentation added as substitute for Vollmers’)

• 9 — Far-field Wake Vortices: Stability and Turbulence, L. JacquinProduction of turbulence inside vortex cores is by short-wave instabilitiesEvidence obtained from shear-layer vortices

• 10 — Wake Vortex decay characteristics and robustness of alleviating devices inatmospheric environments, T. Gerz

Decent simulations showing effect of background turbulence on vortex pairs decay (both 2 & 4vortex systems)

• (presentation cancelled) Investigation on 4 Vortex system with respect to vortex alleviationand consideration of end-effect, H. Vollmers

4-vortex counter-rotating systems using inbd flap edge and/or h. tail for counter-sign vorticesNo mention of practicality of such systems

• 8 — Commemorating our colleague Heinrich Vollmers by his work on wake vortices,Thomas Gerz (abstract not provided; presentation added as substitute for Vollmers’)

• 9 — Far-field Wake Vortices: Stability and Turbulence, L. JacquinProduction of turbulence inside vortex cores is by short-wave instabilitiesEvidence obtained from shear-layer vortices

• 10 — Wake Vortex decay characteristics and robustness of alleviating devices inatmospheric environments, T. Gerz

Decent simulations showing effect of background turbulence on vortex pairs decay (both 2 & 4vortex systems)


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 11 — Wake Vortex alleviation by means of passive vortex devices, C. Bellastrada

Half-model of 4-engine transport tested in tunnelWake survey several spans downstreamTurbulence generators: bluff body, double swept plate, cylinder

• 12 — Assessment of wake vortex control strategies, J. CrouchReview of objectives for vortex control with goal of breakup or modification and decayActive control by oscillating aileronsPassive control by wing-tip devicesFlight simulator studies of vortex encounters to judge utility of various controls

• 13 — State of the current research on wake vortex alleviation, G. VossTow-tank tests at DLR/Goettingen & HSVA/HamburgNumerical calculations by Euler equationsPassive & active alleviation (differential vs. oscillating flaps)

• 11 — Wake Vortex alleviation by means of passive vortex devices, C. BellastradaHalf-model of 4-engine transport tested in tunnelWake survey several spans downstreamTurbulence generators: bluff body, double swept plate, cylinder

• 12 — Assessment of wake vortex control strategies, J. CrouchReview of objectives for vortex control with goal of breakup or modification and decayActive control by oscillating aileronsPassive control by wing-tip devicesFlight simulator studies of vortex encounters to judge utility of various controls

• 13 — State of the current research on wake vortex alleviation, G. VossTow-tank tests at DLR/Goettingen & HSVA/HamburgNumerical calculations by Euler equationsPassive & active alleviation (differential vs. oscillating flaps)


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 14 — Passive Wake Vortex Alleviation, O. Savas

4-vortex counter-rotating system from wing with outboard triangular flapsPIV and flow viz studies in 60m tow tankLong-wave instabilities lead to rapid merging and reduction in vortex strengths

• 15 — Boundary layer control: an effective and feasible method for wake management,D. Greenblatt

Periodic excitation of separated flows over flaps to vary circulation and wake structureExcitation provided by zero mass-flux blowing slotsLow-speed wind tunnel tests demonstrated control of flap separation and thus vortex sheddinglocations, leading to induced instabilities in the vortex wake

• 16 — Effect of continuous and pulsed blowing on the near- to mid-wake flow fieldgenerated behind a simple model and a generic aircraft-type model, E. Coustols

ONERA water tunnel tests, two half-wings facing each other, also VLTA-type modelBlowing types: axial, discrete holes or slots, at flap tip or near aileronAxial jet had modest effect on tip vortexLateral injection more effective than downward injectionDiscrete holes more effective than slots

• 14 — Passive Wake Vortex Alleviation, O. Savas4-vortex counter-rotating system from wing with outboard triangular flapsPIV and flow viz studies in 60m tow tankLong-wave instabilities lead to rapid merging and reduction in vortex strengths

• 15 — Boundary layer control: an effective and feasible method for wake management,D. Greenblatt

Periodic excitation of separated flows over flaps to vary circulation and wake structureExcitation provided by zero mass-flux blowing slotsLow-speed wind tunnel tests demonstrated control of flap separation and thus vortex sheddinglocations, leading to induced instabilities in the vortex wake

• 16 — Effect of continuous and pulsed blowing on the near- to mid-wake flow fieldgenerated behind a simple model and a generic aircraft-type model, E. Coustols

ONERA water tunnel tests, two half-wings facing each other, also VLTA-type modelBlowing types: axial, discrete holes or slots, at flap tip or near aileronAxial jet had modest effect on tip vortexLateral injection more effective than downward injectionDiscrete holes more effective than slots


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 17 — Technical Evaluation, F. Laporte

Objective of workshop was to discuss physics, and we didHave discussed principles of vortex stability for single vortices, systems of vortices,and interactions with jets — mostly covered 4-vortex systemsHave not fully understood the issues

Open issues:Jet-vortex interactions are very important to study and understandStability of vortex systemsVortex control devices—what do they really do, how to make them efficient, practical& robustMust consider applicability and proof of conceptNeed flight test to validate vortex stability theories at realistic Reynolds numbersTranslation of the current understanding to a real aircraft is not fully developed yetNeed to understand the effect of control devices on efficiency of wing designNeed to start thinking about applicability of some of the concepts and their viabilityon actual aircraft

• 17 — Technical Evaluation, F. LaporteObjective of workshop was to discuss physics, and we didHave discussed principles of vortex stability for single vortices, systems of vortices,and interactions with jets — mostly covered 4-vortex systemsHave not fully understood the issues

Open issues:Jet-vortex interactions are very important to study and understandStability of vortex systemsVortex control devices—what do they really do, how to make them efficient, practical& robustMust consider applicability and proof of conceptNeed flight test to validate vortex stability theories at realistic Reynolds numbersTranslation of the current understanding to a real aircraft is not fully developed yetNeed to understand the effect of control devices on efficiency of wing designNeed to start thinking about applicability of some of the concepts and their viabilityon actual aircraft


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 19 — The ONERA Joint Project “Wake Vortex Dynamics”, X. de Saint Victor

Project created in 1997 to focus on fundamental studies100,000 euros/year, 10 persons/yearMain tasks:

Understand wake vortices in near- and far-field, the development of turbulence, instabilities, and means fordestructing the wakeModel wakes by DNS & LES or RANS to study wake evolution, merging, and jet/vortex interactionsSimulate wake encounters with a flight mechanics codeDevelop new measurement techniques such as PIV and LIDAR in various facilities such as catapult or THALESwater tunnel

• 20 — Wake vortex characterization by Lidar technics: catapult and field trials, A. Dolfi-Bouteyre

Lidar measurements in catapult facility and in flightCW Lidar for short-range, pulsed Lidar for ranges over several hundred metersCatapult: A-300 model, 1/20th scale?, speed 23 m/s. Facility: 90 x 20 x 20 m, 50 m usable testsection length

• 21 — Instabilities developing in a wing tip counter rotating vortex pair: experimentalevidence and control, G. Pailhas

Water tunnel tests of vortex pair, two wings mounted on side walls with 1/4c gap between tipsInstrumentation: LDA, PIV, hot wire to measure fluctuation of core velocities

• 19 — The ONERA Joint Project “Wake Vortex Dynamics”, X. de Saint VictorProject created in 1997 to focus on fundamental studies100,000 euros/year, 10 persons/yearMain tasks:

Understand wake vortices in near- and far-field, the development of turbulence, instabilities, and means fordestructing the wakeModel wakes by DNS & LES or RANS to study wake evolution, merging, and jet/vortex interactionsSimulate wake encounters with a flight mechanics codeDevelop new measurement techniques such as PIV and LIDAR in various facilities such as catapult or THALESwater tunnel

• 20 — Wake vortex characterization by Lidar technics: catapult and field trials, A. Dolfi-Bouteyre

Lidar measurements in catapult facility and in flightCW Lidar for short-range, pulsed Lidar for ranges over several hundred metersCatapult: A-300 model, 1/20th scale?, speed 23 m/s. Facility: 90 x 20 x 20 m, 50 m usable testsection length

• 21 — Instabilities developing in a wing tip counter rotating vortex pair: experimentalevidence and control, G. Pailhas

Water tunnel tests of vortex pair, two wings mounted on side walls with 1/4c gap between tipsInstrumentation: LDA, PIV, hot wire to measure fluctuation of core velocities


WakeNet2-Europe

Summaries from Abstracts and NotesSummaries from Abstracts and Notes• 22 — Numerical simulation of exhaust dispersion and contrail formation in the near-field of

an aircraft wake, F. GarnierDNS & LES calculations in near field to evaluate turbulent mixing and vortex dynamics

• 23 — Numerical simulations of wake vortices: i) behind an aircraft-type model, ii) in-groundeffect, and, iii) jet-wake interaction, O. Labbé

Incompressible NS simulations compared to F2 ONERA WT results2-engine model, 1/100 scale, speed = 50 m/sIGE measurements in THALES water tunnelJet-wake interactions by LES

• 24 — Fundamental on vortices: status and perspectives, L. Jacquin(abstract not provided)

• 22 — Numerical simulation of exhaust dispersion and contrail formation in the near-field ofan aircraft wake, F. Garnier

DNS & LES calculations in near field to evaluate turbulent mixing and vortex dynamics

• 23 — Numerical simulations of wake vortices: i) behind an aircraft-type model, ii) in-groundeffect, and, iii) jet-wake interaction, O. Labbé

Incompressible NS simulations compared to F2 ONERA WT results2-engine model, 1/100 scale, speed = 50 m/sIGE measurements in THALES water tunnelJet-wake interactions by LES

• 24 — Fundamental on vortices: status and perspectives, L. Jacquin(abstract not provided)


WakeNet2-EuropeMinix Wing TipMinix Wing TipAfter the workshop, Christian After the workshop, Christian HuguesHugues, inventor of , inventor of Minix Minix wingwingtip, showed ustip, showed us the the Minix Minix tip and explained how it tip and explained how it ““eliminateseliminates””the tip vortex.the tip vortex.(US Patent application 2004/0195461 A1)(US Patent application 2004/0195461 A1)

From From http://www.minix.fr/english/determinating_result.phphttp://www.minix.fr/english/determinating_result.php::

““December 2001, new confirmation in speed uncompressibleDecember 2001, new confirmation in speed uncompressibletests, by numeral simulation of flow arotests, by numeral simulation of flow around an aircraft wingund an aircraft wingequiped equiped oror not with not with Minix Minix device. 25 pages confidentialdevice. 25 pages confidentialreport. These tests occurred at the same realistic flightreport. These tests occurred at the same realistic flightconditionsconditions ((aairspeedirspeed at 100 M/s), Reynolds 7.5 10+6, angle of at 100 M/s), Reynolds 7.5 10+6, angle ofattack attack 44°°. . TrapezoTrapezoïïdal dal wing type Medium lift wing type Medium lift ‘‘EuropaEuropa’’, medium, mediumcord 1164 mm, wing span 8 ( A R ), wing taper of 0.78, 12 %cord 1164 mm, wing span 8 ( A R ), wing taper of 0.78, 12 %Dyckins Dyckins profileprofile.. The official results give: The official results give:

·· An 8% decrease in induced drag. An 8% decrease in induced drag.·· A 5,5 % increase in lift. A 5,5 % increase in lift.·· A 2,4 % increase in fineness. A 2,4 % increase in fineness.·· A 9 % increase of wing span. A 9 % increase of wing span.·· The Vortex is axed on The Vortex is axed on MinixMinix..·· Fluidity of the Vortex coming out of Fluidity of the Vortex coming out of MinixMinix..””


WakeNet2-Europe


WakeNet2-EuropeMinix Wing TipMinix Wing Tip

Numerical streamline calculations with and without Numerical streamline calculations with and without Minix Minix wing tip devicewing tip device

QuickTime™ and aPlan RVB decompressor


QuickTime™ and aPlan RVB decompressor



WakeNet2-Europe

Overall Impressions, ConclusionsOverall Impressions, Conclusions

• Europe has more focused activities in WV research than U.S.• Some of the research addresses far-field vortex behaviors, but

not enough of it in my opinion (on both sides of the Atlantic)Many near-field studies show significant changes in vortices fromeither passive or active alleviation schemesBut these changes may get washed out in mid- and far-field,leaving little or no alleviation achieved

• Seems that they are at as much a loss for a practical alleviationscheme as we are

No wake vortex solution in place for A380…they will flight-test itand measure the wake

• Europe has more focused activities in WV research than U.S.• Some of the research addresses far-field vortex behaviors, but

not enough of it in my opinion (on both sides of the Atlantic)Many near-field studies show significant changes in vortices fromeither passive or active alleviation schemesBut these changes may get washed out in mid- and far-field,leaving little or no alleviation achieved

• Seems that they are at as much a loss for a practical alleviationscheme as we are

No wake vortex solution in place for A380…they will flight-test itand measure the wake

Summary of WakeNet2-Europe WG7 Workshop: “Principles of ... · Don Durston, NASA AmesDon Durston,...

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