PlasmAero-AirTn-sep2013 final publicairtn.eu/downloads/plasmaero-airtn-sep2013_final_public.pdf ·...

3rd AirTN ForumCranfield – 26th-27th september 2013

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PLASMAERO projectPLASMAERO projectPLASMAsPLASMAs for for AEROdynamicAEROdynamic control.control.

Daniel Caruana – ONERA – CoordinatorMaxime Forte – ONERA – WP Leader

33rdrd AirTNAirTN ForumForumCranfieldCranfield University University –– 2626thth 2727thth September 2013September 2013

Hollenstein C.,Boeuf JP, Gleyzes C., Tropea C., Moreau E., Rogier F., Kok J., Choi KS, DonelliR, Leroy A., Cambronne J.P., Zhang X, Mizeraczyk J., Molton P., Séraudie A, …


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Outlines

• Introduction

• Project overview

• Some results

• Summary & Perspectives


3

Outlines

• Introduction


• Some results



4

Project Rationale

Air transport growth + kerosene price increase� Improvement of aircrafts:

- Reduce the fuel consumption

- Reduce the impact on environment (ACARE 2020 and/or after)

Flow optimisation and controlPermanent or temporary adaptation to global and local

aerodynamic conditions

- geometry adaptation- devices (passive, active)How flows can be optimised ?

Need of breakthrough and emerging technology

One way :

Plasma actuators ?


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Plasmas?

Plasmas in the universe:

- One of the four fundamental states of matter- Ionized gas (electrically neutral)

Plasmas are mainly characterized by:- Temperature- Degree of ionization (electron density)

Cold plasmaWeakly ionized

No themodynamic equilibrium

2 different kinds of plasmas used :

Thermal plasmaHighly ionized

Thermodynamic equilibrium


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� Using plasma actuators...why?- Active actuators- Electric energy (fast response time,

easy to control/modulate)

- No mechanical parts (easy installation, low weight)

- High voltages (specific power supplies)

- EMI effects+ -

Shock/BL interaction

Compression wave

Cold plasmans-DBD

BL separation

BL transition delay

Wing tip vortex

Wall jet

(ionic wind)Cold plasmaDBD

BL separationWing tip vortex

High velocityjet

Thermal plasma

PSJ

Aerodynamicapplications

Kind of actuation

Kind of discharge

Actuator

��

��

��

��

��

��

Plasma actuators?


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� The Plasma Synthetic Jet (PSJ) actuator :

Principle :

(1) (2) (3)

1) Energy deposition (arc discharge) � T & P increase2) Jet blowing3) Recovery (natural)

Plasma actuators? (Cont'd)

� The Dielectric Barrier Discharge (DBD) actuator :

Principle : Top view :

> Wall-normal high velocity jet

> Wall-tangent body force


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Outlines

• Introduction


• Some results



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� The PlasmAero Project:- Level 1

- 11 partners in 7 countries in Europe

- Overall budget: 5M€

- UE contribution (FP7): 3.8M€- Duration: 39 months (2009-2012)

- www.plasmaero.eu

- UE project officer : D. Knoerzer

� Main goals of the project:- develop and characterize plasma actuators

- study their interaction with fluid flows (experiments & computations)

- assess their ability to reduce environmental impact of increasing air transport

- integrate most promising actuators on UAVUseful Plasma for Aerodynamic Control

Project overview


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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. SéraudieM. Forte - ONERA)

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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Outlines

• Introduction


• Some results



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WP1 Results Plasma actuators development and characterization

- DBD (classic, sliding, pulsed, VG, multi, saw-like, floating)

HV

Pprime, IMP

- ns-DBD� generation ofcompression wave� sonic velocitypropagation- PSJ

ONERA, LAPLACE

�generation of micro-jet�V up to 300m/s � f up to 2500 Hertz

EPFL, EPEE, LEA, TUD

- VG-DBD

UNOT β=90°67,5°45°22,5°

�IW=3m/s

�IW=10m/s


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- DBD

LAPLACE, ONERA

WP2 Results - Plasma actuators modeling

� 2D code to calculate the body force (NSE+plasma chemistry)� Optimum operating conditions by parametric studies� Validated (vs experiment results)

- ns-DBDLAPLACE

� 2D simulation : capture of the pressure wave� To be validated

- Plasma Synthetic JetONERA

�2D axi-symetric code, 3 steps of modelling(Electric, arc and joule source term)�Arc and micro-jet modeling�Validated, parametric study to perform

Pressure wave formation

Velocity contours

Wall-tangent body force


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WP2 Results – CFD/Plasma-models coupling

Device / flow interaction and aerodynamic application s

� DBD actuator– coupling with CFD through body force

- flat plate: good agreement with the experiment

NACA0015- V0=20m/sWeak TE separation

NACA0012 – U0=6,5m/s – α=8°stream ribbons coloured withx-component of vorticity

� VG-DBD actuator– coupling with CFD through body force

- NACA0015: generation of streamwise vortice�� results qualitatively consistent with experiments

Flat plate - DBD with flow of 5 m/s(Rex = 2.8·10

5)

NLR

• Mid-chord separation control– One aerodynamic configuration:

• NACA0015• U

∞=40m/s, Re c=1,33.106

• AoA α=11,5°

– 3 different actuators, 2 control strategies:• S-DBD (steady) • M-DBD (steady & unsteady) • PSJ � wall-normal jet (VG)

1) DBD insert 2) PSJ insert

� co-flow tangential body force

WP3 Results – Wind tunnel investigations

ONERA, Pprime

• Mid-chord separation controlMain achievements:

1) DBDSteady mode, f AC=1kHz, VAC=20kV

2) PSJfPSJ=750Hz

Baseline

S-DBD

M-DBD

SeparationDelay

14% of chord

26% of chord

Baseline

PSJ ON

SeparationDelay

45% of chord


Pprime ONERA

1) PSJJets blow from wing tip face in spanwise direction

2) DBDMomentum addition at several locations (wing tip, pressure & suction sides)


• Wing tip vortex control– One flow control strategy: modification of transverse velocity component

– Two different actuators:

ONERA, EPEE

ONERA

ONERA, EPEE

• Wing tip vortex controlMain achievements:

1) PSJGlobal effect on the separating shearlayer and on the vortex core up to 40m/s

2) DBDStreamwise vorticity can be either increased or decreased (depending on actuator configuration) up to 20m/s

PS

J O

ffP

SJ

On

U∞=40m/sU∞=10m/s

0.25

U∞=10m/s

U∞=20m/s


ONERA, EPEE

ONERA

stabilisation of the B.L. by velocity profile modification- active wave cancellation (actuation on T.S. waves)- DBD actuator

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)

Hot

wire

RM

S (m

v)

Without plasma

DBD 17 kVolts

Transition delay by steady actuationU0 = 12 m/s �steady actuation: delay due to BL stabilization, 17 % chord

with U0=12m/s (shown with Linear Stability Analysis results)� pulsed actuation

Successful proof-of-concept of AWC in direct frequency mode using closed-loop controlSignificant transition delay observed even at U∞ = 20m/s

ONERA, TUD


Model in WT – DBD actuator

Active wave cancellationU0 = 20 m/s

• Many other results about:– Slat noise control (SOTON)

– B.L. /Shock interaction (EPFL, CIRA)– Leading Edge separation control (EPEE)


PlasmAero Public Website: http://www.plasmaero.eu/List of publications and public documents


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WP4 ResultsUAV – Validation & Integration

UAV definition2D wing model for WT

In-fligh test bench for plasma devices:� Single-DBD �� mass flow (steady)� Multi-DBD �� mass flow (steady)� DBD-VG �� Vortex Generator (steady)

- Integration of HV equipment in a highly EMC sensitive environment. - Miniaturization of the HV generator withmaximized control authority of the actuators

GBS electronic mini-pulse

�� effect on UAV aerodynamics

Inside the fuselage

TUD

In flight


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Outlines

• Introduction


• Some results



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Summary

PLASMAERO contributed to:� develop and characterize plasmas devices (DBD, ns-DBD & PSJ)� understand, modelize plasma actuators with and without external flow

� evaluate plasma technology in acadamic and also realisticconfigurations (in view of industrial application)

� propose recommendations for further studies� publish more than 50 papers

� organize the joint PlasmAero / Ercoftac Workshop, Toulouse 10-12th

December 2013 (Ercoftac bulletin, March 2013)

The Plasmaero results are promising but TRL of the plasma actuators is not high enough to integrate directly on industrial application

PlasmAero Public Website: http://www.plasmaero.eu/List of publications and public documents


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Perspectives

� Device technology and power supply improvement

� Additionnal device development (energy deposition, micro-wave plasmas)

� Assess the overall energy balance (electric consumption VS L/D gain)� Improvement of modeling, particularly in situation of actuation/flow interaction

� Flow-control strategy development: open or closed loop control + unsteady action

� Rise the TRL of plasma actuators in view of future fligth tests


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Thank you. Any questions [email protected]

Coordinator: [email protected]

Useful Plasma for Aerodynamic Control

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