flow control by plasma in plasmaero project

Aerodays 2011Madrid – 30th March – 1st April

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Flow Control by PlasmaFlow Control by Plasmain PLASMAERO in PLASMAERO projectproject

Daniel Caruana - ONERA

AerodaysAerodays 20112011Madrid Madrid –– 3030thth March March –– 11stst April 2011April 2011

Hollenstein C.,Boeuf JP, Gleyzes C., Tropea C., Moreau Eric, Leyland P., Rogier F.,

Kok J., Choi KS, Molton P., Séraudie A., Zhang X., Ott P., Barricau P., Donelli R..


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Outlook

• Why plasmas for aerodynamics?– Needs– Plasma technology

• PLASMAERO project presentation & objectives.

• Project progress, 1st results(one year activities).

• Perspectives.


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Project Rationale

Needs for aircraft improvement:- Performance increase (Flow optimization, weight and consumption

improvement, design simplification, flight operation improvement etc.)- Reduction of impact on environment (ACARE 2020 and after)


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Project Rationale


improvement, design simplification, flight operation improvement etc.)- Reduction of impact on environment (ACARE 2020 and/or after)

Flow optimisation and controlPermanent adaptation to global and local

aerodynamic conditions

One way :


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Project Rationale


improvement, design simplification, flight operation improvement etc.)- Reduction of impact on environment (ACARE 2020 and/or after)

Flow optimisation and controlPermanent adaptation to global and local

aerodynamic conditions

- geometry adaptation- devices (passive, active)

How can flows be optimised ?

Need of breakthrough and Emerging Technology

One way :


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Plasmas devices for Aerodynamics.• considered as active devices (add energy, independent)• various flow control• easy installations & use, very short response time• electric energy use (no compressed air flow)

Plasmas devices for Aerodynamics. Why?


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Plasmas devices for Aerodynamics.

here

• considered as active devices (add energy, independent)• various flow control• easy installations & use, very short response time• electric energy use (no compressed air flow)

� Chosen Plasmas

Plasmas in the Universe:- Temperature of electrons- Density number of charged particles


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Plasmas devices for Aerodynamics.

� PLASMAERO chosen technologies :- Surface plasmas (DBD, ns-DBD)

� cold plasma (weakly ionised, no thermal equilibrium)- Spark plasmas (PSJ)

� thermal plasma (ionised in discharge, thermal equilibrium)

here

DBDNs-DBD

PSJ

• considered as active devices (add energy, independent)• various flow control• easy installations & use, very short response time• electric energy use (no compressed air flow)

DBD: Dielectric Barrier DischargePSJ: Plasma Synthetic Jet


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Dielectric material

PlasmaElectrodesFlow

Dielectric material


V: 1 – 30 kVI: 10 to 20mA, elec. power. ~ 500W/m2

f : 500 à 20000 Hz

� alternating power supplySinusoïdal high voltage

� Roth 90’s years

mass

Upper face Plasmas (positive part)(some micro-discharges)

Lower face plasma

ionic windclose to the wall

How DBD devices work?V

olta

ge (

kV)

Cur

ent (

mA

)


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Dielectric material


Dielectric material


V: 1 – 30 kVI: 10 to 20mA, elec. power. ~ 500W/mf : 500 à 20000 Hz

� alternating power supplySinusoïdal high voltage

� Roth 90’s years

mass

Upper face Plasmas (positive part)(some micro-discharges)

Lower face plasma

ionic windclose to the wall

How DBD devices work?

plasma Force EHD

Ionic wind without flow

EHD= ElectroHydroDynamic

� Production of mass flow: ionic wind

Lagmich Y, Callegari T, Pitchford L, Boeuf JP, J. Phys D: Appl Phys 41 095205 (2008)E. Moreau et all. - J. Phys. D: Appl. Phys. 41 (2008) 115204 (12pp)


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- No use of ionic wind- Voltage increase in a very short rise time � ns- Development of high current streamers

P. Pechske et All.- 42ème Plasmadynamicsand Lasers Conference - AIAA- 27-30 june 2011

How ns-DBD devices work?

Pressure wave generated by the discharge (rise time<100 ns)

EPFL

Phase averaged schlieren images(10 kV, 400 Hz, no flow)

Energy per unit lengh: ~1mJ/cm


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- No use of ionic wind- Voltage increase in a very short rise time � ns- Development of high current streamers

P. Pechske et All.- 42 Plasmadynamicsand Lasers Conference - AIAA- 27-30 june 2011

How DBD-ns devices work?

10-9

10-8

10-7

10-6

10-5

10-4

0

500

1000

1500

2000

2500

3000

3500

14 kV21 kV28 kV35 kV42 kV

Tem

pera

ture

(K

)

Time (s)10

-910

-810

-710

-610

-510

-40

500

1000

1500

2000

2500

3000

3500

14 kV21 kV28 kV35 kV42 kV

Tem

pera

ture

(K

)

Time (s)

�Large part of deposit energyconverted in gas heating

T Unfer & JP Boeuf, Plasma Phys. Control. Fusion 52 (2010) 124019

Pressure wave generated by the discharge (rise time<100 ns)

EPFL

10 ns

0

321P

ositi

on

(mm

) t = 5 µµµµs

12000Pa max

0 6 12mm

Phase averaged schlieren images(10 kV, 400 Hz, no flow)

Energy per unit lengh: ~1mJ/cm


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CEDRE computation

�John Hopkins University, 2002�Onera, 2005

Power supplyHigh Voltage + RC circuitVoltage: 3 to 5000 VoltsCurrent: 1 to 100 mA (mean)

1) Energy deposition (discharge):T, P increase2) Jet blowing3) Recovery (natural)

How PSJ devices work?

Cavity energy deposit = 5mJ


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CEDRE computation

�John Hopkins University, 2002�Onera, 2005

Power supplyHigh Voltage + RC circuitVoltage: 3 to 5000 VoltsCurrent: 1 to 100 mA (mean)

Pototypes –φ 8mm

1) Energy deposition (discharge):T, P increase2) Jet blowing3) Recovery (natural)

D. Caruana et all - AIAA-2009-1307

P. Hardy et all - Plasma - AIAA-2010-5103

How PSJ devices work?

Cavity energy deposit = 5mJ


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Project Identity Card & Consortiumwww.plasmaero.ue

Name: Useful Plasm as for Aero dynamic Control: PLASMAEROStart date: 1st October 2009, 3 years long, Europan framework: FP7Thème: Transport (including Aeronautics)

Activity 1.1.6: Pioneering the Air Transport of the Future

AREA: 7.1.6.1: Breakthrough and Emerging Technologies , AAT.2008.6.1. LiftSmall-scale project, Level 1, Overall budget: 4 988k€, Overall EU contribution : 3 815k€

Consortium composed of:- 7 countries- 11 companies or universities

Project Officer:Dietrich Knoerzer


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Main Project Objectives

• Demonstrate how discharge plasma actuators can be used to control aircraft aerodynamic flow.

(Actuators design, Plasmas physics and Flow physics)• Provide exhaustive recommendations on future work to be performed to

achieve the implementation of this technology.

� Understand, model and classify the most relevant physical characteristicsof plasma actuators capable of influencing flow

� Demonstrate through WT experimentations and CFD the ability of plasma devicesto significantly improve or control the aerodynamics

� Demonstrate the integration of these actuators in a reduced size flight platform andtheir use in real atmospheric conditions


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Work Breakdown Structure

WP5 Dissemination, Exploitation & training (D. Caruana - ONERA)

-

WP0 Consortium Management(ONERA)

Task 0.1 - Consortium Administration(ONERA)

Task 1.1Surface discharges

actuators(CNRS-LEA)

WP1

Plasma deviceinvestigation,development

& improvement

(EPFL)

Task 1.2Spark discharges

actuators(ONERA)

WP2

Physics Modelling and computation

(CNRS-LAP)

Task 2.1Plasma modellingand computation

(EPFL)

Task 2.2Aerodynamic / plasma

coupling(ONERA)

Task 2.3Computational FluidDynamic simulations

(NLR)

WP3 Wind tunnel

investigations for flow control

(ONERA)

Task 3.1Separation(UNOTT)

Task 3.2Wing tip vortex

(ONERA)

Task 3.3Laminar flow &

transition(ONERA)

Task 3.4High lift noise

(SOTON)

Task 3.5Shock/Boundarylayer interaction

(EPFL)

Task 0.2 - Strategic Coordination (ONERA)

WP4 Validation & integration

(TUD)

Task 4.1Take-off and landing flow configuration

(ONERA)

Task 4.2Cruise flow

configuration(CIRA)

Task 4.3Subsonic

Flight Platform(TUD)

-

WP0 Consortium Management(D. Caruana - ONERA)

Task 0.1 - Consortium Administration

Task 1.1Surface discharges

actuators(E. Moreau - CNRS)-

WP1 Plasma devices

Investigation, development& improvment

(C. Hollenstein – EPFLE. Moreau – CNRS)

Task 1.2Spark discharges

actuators(D. Caruana - ONERA)

WP2 Physics Modelling andcomputation

(JP Bœuf –CNRSF. Rogier - ONERA)

Task 2.1Plasma modellingand computation(P. Leyland - EPFL)

Task 2.2Aerodynamic / plasma

coupling(F. Rogier - ONERA)

Task 2.3Computational FluidDynamic Simulation

(J. Kok - NLR)

WP3 Wind tunnel

investigations for flow control

(C. Gleyzes – A. SéraudieONERA)

Task 3.1Separation

(KS Choi - UNOTT)

Task 3.2Wing tip vortex

(P. Molton - ONERA)

Task 3.3Laminar flow &

transition(A. Séraudie - ONERA)

Task 3.4High lift noise

(X. Zhang - SOTON)

Task 3.5Shock/Boundarylayer interaction

(C. Hollenstein - EPFL)

Task 0.2 - Strategic Coordination

WP4 Validation & integration

(C. Tropea - TUD)

Task 4.1Take-off and landing flow configuration

(P. Barricau - ONERA)

Task 4.2Cruise flow

configuration(R. Donelli - CIRA)

Task 4.3Subsonic

Flight Platform(C. Tropea - TUD)


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Outlook

• Why plasmas for aerodynamics?– Needs– Plasma technology

• PLASMAERO project presentation & objectives.

• Project progress, 1st results(one year activities).

• Perspectives.


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Plasma devices – Improvement & Characterisation

- DBD « ionic wind » � classic, sliding, pulsed, VG, multi, saw-like, floating

HV

0 30 60 90 120 1500

2

4

6

8

10

vent

éle

ctriq

ue (

m/s

)

x (mm)

14 kV 1 kHz 16 kV 1 kHz 18 kV 1 kHz 20 kV 1 kHz 24 kV 1 kHz

LEA, IMP

� IW=10m/s

N Benard, A Mizuno and E Moreau, J. Phys. D: Appl. Phys. 42 (2009) 235204Podliński J. et all. 12th Int. Symp. on High Pressure Low TemperaturePlasma Chemistry, 2010, pp. 74-78.


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Plasma devices – Characteristics & Physics


HV

LEA, IMP

- ns-DBD

IW=10m/s

�generation of compression waveP~10000 Pa, sonic velocity propagation

EPFL, LEA, TUD, EPEE

P. Pechske et All.- 42 Plasmadynamics and Lasers Conference - AIAA- 27-30 june 2011

Phase averaged schlieren images (10 kV, 400 Hz, no flow)


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Plasma devices – Characteristics & Physics

t (sec.)

V(V

olts

)

-1.0E-04 .0E+00 1.0E-04 2.0E-04 3.0E-04 4.0E-04 5.0E-04-1

0

1

2

3

4


HV

LEA, IMP

- ns-DBD

IW=10m/s

�generation of compression waveP~10000 Pa, sonic velocity propagation

- PSJ

ONERA, LAPLACE

0

50

100

150

200

250

300

0 200 400 600 800 1000 1200 1400 1600

V jet (C=6 nF)

V jet (C=10 nF)

V jet (C=20 nF)

V jet (C=30 nF)

V up to 300m/s (T=400K)f up to 2500 Hertz

P. Hardy, P. Barricau, D. Caruana, C. Gleyzes, A. Belinger, J.-P. Cambronne. Plasma - AIAA-2010-5103

EPFL, LEA, TUD, EPEE

Vel

ocity

Frequency


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Aerodynamic applications - Separation

� strategy: bring flow momentumto B. L.

- Fluidic injection by micro-jet = vortex generator (DBD, PSJ)

U. Nottingham – Flow visualisation – dif. Yaw angles – U0=1,5m/s

β=90° 67,5° 45° 22,5°

ONERA – PIV measurements –α=45°, β=60° – U0=40m/s – VJSP=230m/s

DBD – IW=1,5m/s – U0 � 17m/sPSJ – V=230m/s – U0=40m/s

Nottingham U.ONERA


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X (mm)

Y(m

m)

-1 0 1 2 3 4 50

10

20

30

40

50

JSP OFF (reference case)

JSP ON (750 Hz)

JSP ON (50 Hz)

JSP ON (250 Hz)

Uo=20m/sAlpha=13°

ONERA – PIV measurements –α=30°, β=60° – U0=20m/s – VJSP=200m/s

B.L. profile close to T.E.

� 1st results with PSJ – V=230m/s – U0=20m/sWake

X (mm)

Y(m

m)

0.4 0.5 0.6 0.7 0.8 0.9 1-100

-50

0

50

100

JSP OFF (reference case)

JSP ON (750 Hz)

JSP ON (50 Hz)

JSP ON (250 Hz)

Uo=20m/sAlpha=13°

- NACA0015 – Fixed transition – Re=0,8M - T.E. separation (Onera)


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- Fluidic injection by layer (#DBD) – 1st results

OFF ON

- NACA0015 – T.E. separation (LEA) IW=6m/s, V0=20m/s

- NACA0012 – L.E. separation (EPEE)

IW=5m/s, V0=40m/s

Leroy & all - The 20th International Symposium on Plasma ChemestryUSA – July 24-29, 2011

Plasma ON


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Aerodynamic applications – Wing tip Vortex

� strategy: transversal velocity control

- PSJ

- DBD

� displacement of the vortex core& decrease of longitudinal vorticity

U0=20m/s (Onera)

# configurations

ONOFF

OFF ON

� decrease of longitudinal vorticity

U0=10m/s (Onera, Epee)

3D Onera-D model


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Aerodynamic applications – Laminarity

� strategy: stabilisation of the B.L. by velocity profile modification (IW)

DBD actuator X/C = 10%

Hot wire probe

Flow

Transition location on ONERA D upper side Alpha = 2.5° U0 = 12 m/s Plasma f = 2 KHz

0,0

0,2

0,4

0,6

0,8

1,0

0 100 200 300

X (mm)H

ot w

ire R

MS

(mv)

Without plasma

DBD 17 kVolts

Transition location on ONERA D upper side Alpha = 2.5° U0 = 7 m/s Plasma f = 2 KHz

0,0

0,2

0,4

0,6

0,8

1,0

0 100 200 300

X (mm)

Hot

wire

RM

S (m

v)

Without plasma

DBD 8.5 KVolts

DBD 12.7 kVolts

DBD 17 kVolts

U0 = 7 m/s U0 = 12 m/s

‘natural’ transition onset

2D Onera-D model

A. Séraudie.- 41st AIAA Fluid DynamicsConference and Exhibit- AIAA- 27-30 june 2011

ONERA


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Aerodynamic applications – Slat Noise

A. wake of cusp

B. region where the free shear layer converges with the stream coming from the stagnation point on the main element

C. wake off the trailing edge

D. gap flow, and an intensive source

α = 6°, V0 = 25 m/s

Plasmas onS

PL

(dB

)

frequencyDBD actuatorlocated in zone A

Xinfu Luo and Xin Zhang.- 41st AIAA Fluid DynamicsConference and Exhibit- AIAA- 27-30 june 2011

Southampton U.


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Summary

� Plasmas devices and physics (#DBD, DBDns and JSP)� simple utilization, active & small, electrical� very short response time� characterizations and diagnostics, modeling

� PLASMAERO project and 1st tests results� encouraging, actually in progress

- Devices improvement- Flow control applications (separation, tip vortex, laminarity, slat noise)

D. Caruana, Plasma Phys. Control. Fusion 52 (2010) 124045


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Perspectives

� PLASMAERO perspectives (� 18 months)� Control strategy, plasmas physics and flow interaction physics definition (tests and CFD) � How it works?� 3D flow configurations for separations and laminarity� DBDns in transonic flow conditions (larger scale)� Subsonic flight platform (4m span, 20-30m/s)

Devices locations

Power supply& flight control system

Darmstadt U.


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• Thank you for your attention

Daniel Caruana (ONERA)[email protected].: +33 5 62 25 28 57

flow control by plasma in plasmaero project

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