LASMA

F

PI

AS

LASMA

NDUCED

LOW

ERODYNAMIC

TRUCTURE

http://my.fit.edu/eflow/

Project GoalProject Goal

Analyze, design and build an aerodynamic structure which will improve performance by implementation of plasma actuators with optimum aerodynamic conditions along with corresponding efficiency regimes.

Objectives

• To improve critical angle of attack by >20%• Augment Lift vs. Drag ratio by > 15%• Increase Fuel efficiency by 0.5%• Optimize weight vs. takeoff and landing

distance ratio• Determine cost-effectiveness of this system

1% reduced drag Boeing 727 = 20,000 gallons of fuel per year = OVER $100,000.00 savings/airplane

[Ref. 2]

Project Approach

Literature reviewCalculationsExperimentationDesignConstructionOptimization

Project Approach

Literature review- Collect published research papers- Extract fundamental information- Characterize system- Develop theory

Project Approach

Literature reviewCalculations

- Specify material’s characteristics- Develop variable’s range

• Voltage V, frequency f, etc.

Project Approach

Literature reviewCalculationsExperimentation

- Conduct Preliminary tests• CTE, Thermal threshold, Dielectric Constant

- Collect performance data• Coefficient of Lift c L, Coefficient of Drag c D, Stall Angle α Stall, Ionization freq.-volt., etc.

Project Approach

Literature reviewCalculationsExperimentation

- Collect performance data• Wind tunnel testing

Strain gage force balance Wake survey method

Project Approach

Literature reviewCalculationsExperimentationDesign

- Analyze data- Corroborate results

Project Approach

Literature reviewCalculationsExperimentationDesignConstruction

- Build test models- Flat plate, NACA 0015 airfoil(s)

- Fabricate final product

Project Approach

Literature reviewCalculationsExperimentationDesignConstructionOptimization

- Revise design criteria- Publish results

Current Date

Design Specifications Metrics Units ValueDielectric Material High Dielectric Constant - 3.5

Dielectric Material Resistivity Ohms > 10,000

Width of the Structure Test Piece Wind Tunnel Width (UCF vs. FIT) m < 0.5334 (21)

Length of the Structure Test Piece Wind Tunnel Length (UCF vs. FIT) m > 1

Shape of airfoil (NACA profile) Large Curvature - NACA 0015

Uniform Ionization of air Variable Frequency Range Hz

Uniform Ionization of air Actuator Width mm 5

Uniform Ionization of air Voltage Range V

Uniform Ionization of air Electric Field Strength V/m

Actuator Shape Ionization Effects -

Actuator Material Conductivity μS/m 59.6

Optimal Plasma Profile Actuator Gap Width m

Optimal System Configuration Actuator Layout and Count N/W·kg

Instrument Shielding Electromagnetic Field Tesla/m

Operation at commercial airliner cruising speeds Reynolds Number Re 6 x 107

Low Energy Consumption Circuit Characteristics J/m

Design specs

wind

tunnel

testing

Force balance method

MaterialsExperimental procedureActuator ConfigurationResultsRevision/Optimization

Experiment setup

MaterialsG10 fiberglass plate- 18.0” x 9.0” x 0.25”Kapton tape- 18” x 1.75” x 0.40”Copper foil

• Anode: 18.0” x 0.20” x 0.02”• Cathode: 18.0” x 0.79” x 0.02”

Experimental ProcedurePreliminary flat-plate Construction

• G10 fiberglass composite• 18”x 9”x 0.25” dimensions • Copper foil installation • Electronic link

Wind tunnel Set up • Attach components• Align/ Calibrate instrumentation

Force balance method

Actuator configurationMultiple actuator configurations

Actuator Chord wise Position (y/c)*

Trial 1

Trial 2

Trial 3

Trial 4

Trial 5

Trial 6

Trial 7

Trial 8

1 0 OFF ON OFF OFF ON ON OFF OFF

2 0.465 OFF OFF ON OFF ON OFF ON OFF

3 0.93 OFF OFF OFF ON OFF ON ON OFF

* Chord length c = 9 in

Force balance method

Actuator configuration• Multiple actuator configurations• Experiment variables

FixedGap width gActuator width wActuator thickness tFree stream velocity V

ControlledActuator Location y/cFrequency fVoltage VAngle of Attack α

Force balance method

Results Revision/OptimizationData Analysis

• Coefficient of lift• Coefficient of Drag• Stall angle

Graph Results

Force balance method

Experiment #1 setup

Flat Plate with actuators (Top view)

Copper foil anode

Copper foil cathode

2

Experiment Layout

Flat Plate with actuators (Right view)

Kapton Tape

G10 Fiberglass

Experiment #1 setup

Reserved for ProE picture

Overall view of the flat plate with actuators

Experiment #1 setupTest Section (21” x 21”)

Florida Tech Low-Speed Wind Tunnel [Ref: 6]

DAQ/ LabVIEW

Force Balance of Wind Tunnel [Ref: 6]

Calibrating Arm/ Weights

Coefficient of Lift:

Coefficient of Drag:

Reynolds Number:

CL: Coefficient of Lift CD: Coefficient of DragRec: Reynolds Number L: Lift ForceD: Drag Force ρ: Free stream densityU: Free stream velocity S: Surface area𝜇: Viscosity c: Plate with

Exp #1 Calculations

Theoretical value of the CL and CD of a flat plat at O° Angle of Attack and Re of 10,000 [Ref 7]:

`Implementation:

• Easily modify existing structure• Structurally sound

Discharge:• Greater effect per actuator• Easy to build• Variable test conditions

Safety:• Reduce risks to humans•Failsafe mechanisms• Safe manufacturing

Electronics

FREQUENCY

DC supply. Needs AC/AD converter

Cannot be lower than 1Khz =

Residual Current

VOLTAGE

0 to 1000VDC,

POWER

20W

Current system

ULTRAVOLT High Voltage Power SupplyItem number: 180293665388

$100.00 + Shipping and Tax Reference [12]: www.ultravolt.com ;

References1. SUBSONIC PLASMA AERODYNAMICS USING LORENTZIAN MOMENTUM TRANSFER IN

ATMOSPHERIC NORMAL GLOW DISCHARGE PLASMAS - J. Reece Roth([email protected]), Hojung Sin ([email protected])and Raja Chandra Mohan Madhan - UT Plasma Sciences Laboratory

2. PIFAS Team - http://www.kinema.com/actuator.htm - POTENTIAL FLOW MODEL FOR PLASMA ACTUATION AS A LIFT ENHANCEMENT DEVICE - Kortny Daniel Hall - University of Notre Dame

3. Google Images4. Flow control in low pressure turbine blades using plasma actuators - - Karthik Ramakumar,

Arvind Santhanakrishnan, Jamey Jacob - University of Kentucky5. Flow Control And Lift Enhancement Using Plasma Actuators - Karthik Ramakumar and

Jamey D. Jacob†- AIAA-2005-4635 - Fig 136. PIFAS Team7. A Computational Study of the Aerodynamic Performance of a Dragonfly Wing Section in

Gliding Flight, Abel Vargas, Rajat Mittal and Haibo Dong, The George Washington University, 23/05/2008.

8. http://en.wikipedia.org/wiki/Electrical_resistivity 9. http://www.aoe.vt.edu/~mason/Mason_f/A380Hosder.pdf10. http://www.kaptontape.com/tech_pages/1mil_polyimide_sheets.php11. http://www.pstc.org/papers/pdfs/McAlees.pdf12. http://www.ultravolt.com

Group Members Gonzalo Barrera

Esteban Contreras

Joseph Dixon

Andres Fung

Sumit Gupta

Georgio mahmood

Ivan Mravlag

Christian O. Rodriguez

Septinus Saa

For more information please visithttp://www.my.fit.edu/eflow