An overview of European projects on Wake Vortices(in connection to Working Group 7 activities"Principles of Wake Vortex alleviation")

Eric COUSTOLSONERA / DMAE – Toulouse - France

With contributions fromClaudio Bellastrada, Anton de Bruin, Fabrizio de Gregorio, Gerry Elphick,Bram Elsenaar, Thomas Gerz, Caren and Klaus Huenecke, Laurent Jacquin,Jens Koenig, Florent Laporte, Thomas Leweke, Guy Pailhas,Katrin Schmidt & Heinrih Vollmers

WakeNet2-Europe

WakeNet2-Europe - WG7 Workshop - Toulouse – 9-10 February 2005 - 1

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Wake Vortex Research in EuropeContext

EUROPE has been highly involved in Wake Vortex research, fromcomplementary studies undertaken in the framework of:

BRITE-EURAM 4th, 5th & 6th FP Projects [Eurowake (‘96 ‘99),WAVENC (‘94 ‘97), C-Wake (‘00 ‘03), S-Wake ('00 '03), Far-Wake('05 '07)] ; Technology Platforms [AWIATOR (‘02 ‘07)] ; ThematicNetworks [WakeNet ('98 ‘01) & WakeNet2-Europe (‘03 ‘06)] National programmes/activities:

ONERA Joint Research Project (‘97 ‘04), DPAC programme(Civil aircraft applications) (‘00 ‘05)DLR Wirbelschleppe Project (‘00 ‘05)DLR/ONERA Collaborative Research Programme on aircraftwake vortices Minimised Wake: Phases I ('99 '02) & II ('03 '06)NLR – CERFACS – NATS activities; TsaGI too

Industrial research (Airbus Industrie, 3E partners)

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EUROWAKE

near field vortex

WAVENC

encounter modeling

M-FLAME

on board detection

C-WAKE

wake characterizationS-WAKE

safety assessment

AWIATOR

minimizing by design

I-WAKE

on board detectionWakeNet

WakeNet 2-Europe

European wake vortex related programs

WakeNet -USA

FAR-WAKE

Fundamental aspects

ATC-WAKE

ATM implementation

STILL ACTIVE

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Wake Vortex Research in EuropeContext

Characterization, wake decay, design for more benign aircraft wakes

Application of reduced aircraft separations

FAR-Wake

Eurowake C-Wake AWIATOR T1.1

S-Wake ATC-Wake

WakeNet WakeNet2-Europe

WakeNet-USA

WAVENC S-Wake 2 ??

WakeNet3-Europe ??

European partners have thus defined pluri-annual research programs whichconcentrate on complementary aspects:

characterisation of WV formation, evolution (physics, dynamics) & decay,development of strategies for wake vortex control, minimisation

(Picture from T. Leweke )

WG7

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Vortex field: generally split in four regions

Region I: Near-wake field (few wing chord lengths) Vortex formation

Region II: Extended near-wake field (~10 b) Vortex roll-up & merging

Region III: Mid-wake field ( 80 b) Vortex drift - instabilities appearance

Region IV: Far-wake field (> 100 b) Vortex collapse, disperse Development of instabilities

Wake Vortex DynamicsField description

1b 10b 100b

LIDAR

(150b ~ 4 n.m. separation distance behind LTA aircraft)

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III

IIIIV

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Wake Vortex DynamicsField description in the mid-wake region from Catapulte

Model under the ramp at B20

B20 Catapult Facility(ONERA Lille)

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Wake Vortex DynamicsField description in the mid-wake region from Towing Tank

Model at TUDelft

C-Wake

Movie provided by:

Model at INSEAN

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What do we know about Wake Vortex Alleviation?State of the art (from "ToR" Terms of Reference of WG7)

Wake Vortex formation and roll-up reasonably well understoodthough some uncertainty still present in the accurate prediction ofthe vortex strength for particular aircraft configuration

Mechanisms for Wake Vortex alleviation studied extensively in thenear-/extended near-wake field but not so much in the mid- to far-wake field. Thus:

effectiveness on decay phase has to be clarified from groundbased facility tests (i.e. towing tank, catapult)effectiveness for full scale aircraft has still to be provenvalidation from CFD applications is needed

Problems of patents issues

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Alleviating wake vortices means:

Near-field: to promote small scale instabilities and increase diffusion of vorticity or to introduce turbulence in vortex cores to obtain thicker final vortices (larger cores but less intense smaller rolling momentum)

Devices: spoilers, wing-/flap-tip, fence...

Far-field: to promote long-wave instabilities and trigger perturbations to obtain a premature wake collapse

Passive concept: Multiple-vortex system (Flap arrangement)

Active devices: Blowing, oscillating flaps,ailerons or spoilers

What do we know about Wake Vortex Alleviation?Lessons learnt from European Projects & National Programmes

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0goal 1* ≈NewT

Near-field: Γ unchanged but lower rolling momentum expected(encounters with the vortices before T * or with vortex pieces after T * )

*NewT

near-field

far-field

*NewT

near-field

far-field

Far-field : wake collapse due to long-wave instabilities

What do we know about Wake Vortex Alleviation?Two main strategies

0/* tTT =

0200 /2 Γ= bt π bsb .0 =

ARsCxt L34** π=

Γ5-15/Γ0

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1

(Pailhas et al., 2000)

What do we know about Instability in Wake Vortex?Short- and long-wave instability

b=c/4

E.

x/b=33

E/E0.

(Hot-wire measurements)Widnall instability

Short-wave:(λ~O(a)~core radïus~5mm)

Crow instability

Long-wave:(λ~O(b0)~30mm)

(by courtesy of G. Pailhas – ONERA)

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2

short wave (Widnall)

long wave (Crow)

Leweke & Williamson 1997

What do we know about Instability in Wake Vortex?Short- and long-wave instability

(by courtesy of T. Leweke – IRPHE)

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short-wave instabilities (Widnall type) control the merging ofco-rotating vortex systems (e.g. tip / flap)

several W/T tests have been performed on this topic but, some patents

short wave (Widnall) ? Merger

Meunier & Leweke 2002

What do we know about Wake Vortex Alleviation?Near-field control

(by courtesy of T. Leweke – IRPHE)

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vortex merging can be controlled by devices, if needed

short-wave instabilities (Widnall type) control merging of co-rotating vortex systems (e.g. wing tip / flap tip)

several ground tests were performed on this topicalthough some patents have been issued, limitinginformation, yet.

What do we know about Wake Vortex Alleviation?Near-field control

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What do we know about Wake Vortex Alleviation?Near-field control (Examples of devices)

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What do we know about Wake Vortex Alleviation?Near-field control works

Experiments in DNW-NWB showed:- a reduction of peak vorticity,- a reduction of max cross-flow,- an enlargement of vortex core, though some centres not well defined (turbulence generator)

Generally speaking:- spread of vorticity but- Γ flap vortex remains unchanged

Flap Tip Modifications at X/b=0.5

(by courtesy ofE. Stumpf – DLR-Bs)

C-Wake

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What do we know about Wake Vortex Alleviation?Near-field control works

OFVOFVOFVOFV

Device

(by courtesy ofC. Bellastrada – TU Munich)

Non-dimensionalaxial

vorticitydistributions for

ReferenceConfiguration

and

DeviceConfiguration

x*

t*

ξ

0 1 2 3 4 5 6 7 8

0 0 .0 3 1 0 .0 6 2 0 .0 9 3 0 .1 2 4 0 .1 5 5 0 .1 8 6 0 .2 1 7 0 .2 4 8

0

1 0

2 0

3 0

4 0

5 0

6 0

R e fe re n ce (F L M )R e fe re n ce (D N W )F la p p la te (F L M )R ig h t sw e p t p la te M R (F L M )L e ft sw e p t p la te M L (F L M )D o u b le sw e p t p la te D D (F L M )

re d u ctio n inp e a k va lu e

M e rg in g o fO N V w ith O F V

S ta rt o f m e rg in g o fW T V w ith O F V -O N V

5 2 %

Device

Non-dimensional axial vorticity peak ξξ ofOutboard Flap Vortex (OFV) vs. X/bfor Reference & Device configurations

at X/b = 5.56

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X/b=1 X/b=5

withoutdevices

withdevices

Flap- & wing-tip devicesby courtesy of Airbus France

E2-type a/c model (1:100 scale)ONERA F2 W/T - CL=1.7

EUROWAKE

vorticity - LDV /ONERA

What do we know about Wake Vortex Alleviation?Near-field control ... may be hopeless

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What do we know about Wake Vortex Alleviation?Near-field control ... is subtle

Basic, config 1 Spoiler, config 2 Spoiler, config 3

SWIM model atDNW-LST W/T

(by courtesy ofA. de Bruin - NLR)

PIV cross flow velocity at X/b=10

Almost merged Not merged Fully merged

C-Wake

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What do we know about Wake Vortex Alleviation?Near-field control ... is subtle

Basic, config 1 Spoiler, config 2 Spoiler, config 3

PIV cross flow velocity at X/b=30 (SWIM model at DNW-LLFT W/T)

C-Wake

(by courtesy ofA. de Bruin - NLR)

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What do we know about Wake Vortex Alleviation?Near-field control ... using jets (cold dynamics)

Power for Level Flight(40,000 r.p.m.)

Approach Idle(20,000 r.p.m.)

5-Hole probe at X/b=0.294 & 1.322

C-Wake Filton Low Speed W/T

Effect of Power Increase(by courtesy of

G. Elphick – Airbus-UK)

Reductionof vortexintensity

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What do we know about Wake Vortex Alleviation?Near-field control ...using jets (cold dynamics)

C-Wake

Effect of Power Increase

(by courtesy ofE. Stumpf)

Euler computations (Tau-code):- VLTA-type model- ~6 Million grid (unstruct.)

strong interaction of the outer flapvortex with the outer engine jetEngine jet wrapped around flapvortex and about to be trapped invortex core region

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What do we know about Wake Vortex Alleviation?Near-field control ... to affect Far-field

Device

C-Wake (by courtesy of K. Huenecke, C. Huenecke & K. Schmidt – AI-D)

INSEAN Towing Tank

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What do we know about Wake Vortex Alleviation?Far-field control

Problem:large wavelength (Crow) can be considered and exploited for reducing wake vortex lifetime forcing instabilitiesAbility of Crow instability to rapidly decrease potential danger of a 2-vortex system is not obvious because of low growth rate

Idea: to promote long-wave instabilities and to trigger perturbations to obtain a premature wake collapse

Solutions: Long-wave instabilities are very powerful if the number of vortexpairs is greater than one: multiple vortex system realised by wingspan loading (DFS, spoilers) and enhanced by HTP loading, devices

Trigger instabilities via blowing devices ONERA Joint ProjectDLR ONERA CRP

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What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system

1b

1 2 43

1Γ 2Γ

2b

Half-wake

Evidence from CFD of producing a counter-rotatingvortex pair

initial condition measured byDNW-NWB, enhanced and

post-processed by UCL

roll-up calculation by UCL withvortex filament method indicatingdouble vortex pair with counter-

rotating vortices x/b = 25

can be used to detect "rapidly" the interesting cases

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When two pairs of counter-rotating vortices can be formed– strong interaction between the vortex pairs– leading to instabilities & a non-linear development (OMEGA-loops)– that destroy the vortices due to a strongly increased dissipation

What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system

Example of OMEGA-loops as calculated with 3-D (non-viscous) vortex method

(by courtesy ofG. Winckelmans – UCL)

Consistent with former exp.evidence in towing tank

(Savas, Durston et al.)

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-1 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 0-0.6

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Y/(b/2)Z/

(b/

ΩX (b/2)/U∞

X/b=1

6264/6265 tests

g

CL=1.165- U∞=30 ms-1 - α =12.00o

no H.T.P-1 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 0

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Y/(b/2)

Z/(b

/2)

ΩX (b/2)/U∞

X/b=1

6305/6306 tests

VLTA-BASIC configurationCL=1.4 - U∞=30 ms-1 - α =7.92o

no H.T.P

-1 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 0-0.6

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Y/(b/2)

Z/(b

/

ΩX (b/2)/U∞

X/b=1

g

CL=1.4 - U∞=30 ms-1 - α =11.22o

no H.T.P

VLTA-BASIC

Experiments (3D LDV) showed:- real potential for modifying wake evolution in extended near-wake

field (effect on secondary flow)- generation of 4-vortex system

Outboard loading

VLTA-1

VLTA-5

Inboard loading

What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system

VLTA-type model (1:50)ONERA F2 W/T - CL=1.4

C-Wake

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What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system C-Wake

Trajectorymeasurements(tomoscopy,

ONERACatapulte B10)

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VLTA-1

VLTA-5

Real strong potential of suchwing loading modificationsfor altering vortex trajectories

Trajectory measurements (tomoscopy, ONERA Catapulte B10)

X /B

D/2

0 5 10 15 20 25 30 35 40 45 50 55 60 650

0.05

0.1

0.15

0.2

0.25

0.3

0.35

0.4

0.45

0.5

0.55

0.6

BasicVLTA-1VLTA-5

X /B

H

0 5 10 15 20 25 30 35 40 45 50 55 60 65

-1 .8

-1 .6

-1 .4

-1 .2

-1

-0 .8

-0 .6

-0 .4

BasicV LT A-1V LT A-5

Lateral spacing of main vortices Height of main vortices

Ground effect

What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system

C-Wake

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testing different solutions (LES)

What do we know about Wake Vortex Alleviation?Far-field numerical control via Multiple-vortex system

forced long-wave (Crow) optimal

Vortices still remain strong

(by courtesy ofL. Jacquin – ONERA/DAFE and E. Stumpf – DLR)

1b

1 2 43

1Γ 2Γ

2b

Half-wake

Greater Energy Drop

t*~1.8

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What do we know about Wake Vortex Alleviation?Far-field numerical control via Multiple-vortex system

(by courtesy of E. Stumpf – DLR)

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What do we know about Wake Vortex Alleviation?Far-field control via HTP Loading

Model setup for generating a 4 wake vortices systemModel setup for generating a 4 wake vortices system

generic airfoil + tail-plain (negative incidence)

In memory ofIn memory ofHeinrich...Heinrich...

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What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system

Flow visualisation of the wake flow fieldsFlow visualisation of the wake flow fieldsLeft: the wake vortex pair of theprinciple airfoil.The circulation (vortex core) keepsits intensity for more than 60 spans

Right: The two additional vortices addedto interact with the main wake vorticeswhich interact within 30 spans

(view from bottom of tank)

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What do we know about Wake Vortex Alleviation?Far-field control via Multiple-vortex system

Vortex peak velocity

x/b

x/b

Vortex core sizeSpan Loading Variation

(by courtesy ofAirbus-D)

HSVA Towing Tank

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Further Research on Wake Vortex AlleviationWhat are the unsolved issues?

Testing facilities:To check if a selected near-wake field device really changes thevortex size/width and consequently the rolling momentum at theend of the diffusion regime To confirm that wake vortex break up observed in some facilities,resulting from "Optimised Wing Span Loading", are really attributedto long-wave instabilities and not to "installation- or end-effects"To set-up the knowledge base for strategies of Wake AlleviationTo answer the questions:

Is there any potential effect that we can expect from vortexinteraction with jets in view of accelerating its decay?Can turbulence be tuned out to enhance decay? ends-effects, bursting, ....

....

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Further Research on Wake Vortex AlleviationWhat are the unsolved issues?

CFD tools:To evaluate the potential of simplified simulations, e.g. vortexmethods for defining strategy for Wake Vortex AlleviationTo evaluate the potential of actual CFD tools to capture theexperimentally recorded vortex roll-up, formation and evolutionphases, from input provided by data bases (generated in theframework of European programs)To evaluate the sensitivity of vortex roll-up and merging to meshresolution, longitudinal domain extent or initial perturbation....

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Further Research on Wake Vortex AlleviationWhat are the unsolved issues?

Aircraft applications:To confirm Wake Vortex alleviation with flight tests (with appropriatevalidated technique: ground or in-board Lidar?To evaluate the potential of long wave mechanism robustness toweather conditionsTo evaluate the effect of atmospheric impact (cross-wind, thermalstratification, wind shear, turbulence, ground)...

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Aircraft WIng with Advanced Technology OpeRation AWIATORProgramme target is the proof of concept and in-flight validation ofmature wing technologies for future transport aircraft application.

AWIATOR is a "Technology Platform" within the 5th Framework Programme of the EC

Programme duration: 2002 – 2007

Programme managed by Airbus D

23 partners from Europe (+Israel) plus several subcontractors participate:Airbus D, F, UK, HQ; DLR, ONERA, NLR; EADS LG, M; Alenia, Sonaca, GKN,Sener, Spasa, IAI; CNRS, Cerfacs, Inasco, IST, UCL, NTUA, TUB, TUM(Countries: De, Fr, UK, NL, It, Be, Es, Pt, Is)

(by courtesy of J. Koenig – Airbus-D, ECCOMAS 2004 Conference)

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Strategy:• Calculations Near & Far Field Flow• Standard Ground Tests Wind Tunnel• Advanced Ground Tests Water Tank, Catapult• Flight Tests Ground & In-Flight Meas‘ts

Objectives for Wake Vortex Research (T1.1)• Gain Knowledge: How to measure aircraft‘s

wakes, how to rate aircrafts in the designstage

• Check Chance for Manipulation: Toaccelerate vortex decay by active or passivemeans: design, devices, configuration

Task 1.1: Wake Vortex Devices (by courtesy of Jens Koenig, Airbus-D)

(by courtesy of J. Koenig – Airbus-D, ECCOMAS 2004 Conference)

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FAR-Wake: FundamentAl Research on Aircraft Wake Phenomena

• Specific Targeted Research Project (STREP) – 6th FP Programme• Starting date: 1 February 2005 (3 years)• Participants: 10 universities, 6 research centers, Airbus• Coordinator: Thomas Leweke

Objectives• gain new knowledge about open issues of vortex dynamics relevant to aircraft wakes• improve physical understanding

• short term:- more precise wake characterization methods (ground testing, CFD, flight tests)- more reliable wake prediction tools (ATM context)

• long term:- knowledge base for strategies of wake alleviation

(by courtesy of T. Leweke – IRPHE)

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Strategy:• study of generic / simplified configurations

• multiple complementary approaches:

- theoretical analysis

- experiments (mostly small-scale)

- CFD

- analysis of existing data

• emphasis on physics

Work Package 1: Vortex instabilities and decayWork Package 2: Vortex interactions with jets and wakesWork Package 3: Wake evolution near the groundWork Package 4: Synthesis and Assessment

(by courtesy of T. Leweke – IRPHE)

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