LASMA

1. http://my.fit.edu/eflow/ P LASMA I NDUCED F LOW A ERODYNAMIC S TRUCTURE

2. Project 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.

3. 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

4. [Ref. 2] 1% reduced drag Boeing 727 = 20,000 gallons of fuel per year = OVER $100,000.00 savings/airplane

5. Project Approach Literature review Calculations Experimentation Design Construction Optimization

6. Project Approach Literature review • Collect published research papers • Extract fundamental information • Characterize system • Develop theory

7. Project Approach Literature review Calculations • Specify material’s characteristics • Develop variable’s range • Voltage V, frequency f, etc.

8. Project Approach Literature review Calculations Experimentation • 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.

9. Project Approach Literature review Calculations Experimentation • - Collect performance data • Wind tunnel testing Strain gage force balance Wake survey method

10. Project Approach Literature review Calculations Experimentation Design • Analyze data • Corroborate results

11. Project Approach Literature review Calculations Experimentation Design Construction • Build test models • Flat plate, NACA 0015 airfoil(s) • Fabricate final product

12. Project Approach Literature review Calculations Experimentation Design Construction Optimization • Revise design criteria • Publish results

13. Current Date

14. Design specs

15. wind tunnel testing

16. Force balance method Materials Experimental procedure Actuator Configuration Results Revision/Optimization

17. Experiment setup Materials • G10 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”

18. Force balance method Experimental Procedure Preliminary 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

19. Force balance method Actuator configuration Multiple actuator configurations

20. Force balance method Actuator configuration • Multiple actuator configurations • Experiment variables • Fixed • Gap width g • Actuator width w • Actuator thickness t • Free stream velocity V • Controlled • Actuator Location y/c • Frequency f • Voltage V • Angle of Attack α

21. Force balance method Results Revision/Optimization Data Analysis • Coefficient of lift • Coefficient of Drag • Stall angle Graph Results

22. Experiment #1 setup Copper foil anode 2 Copper foil cathode Flat Plate with actuators (Top view)

23. Experiment Layout Kapton Tape G10 Fiberglass Flat Plate with actuators (Right view)

24. Experiment #1 setup Reserved for ProE picture Overall view of the flat plate with actuators

25. Florida Tech Low-Speed Wind Tunnel [Ref: 6] Force Balance of Wind Tunnel [Ref: 6] Experiment #1 setup Test Section (21” x 21”) Calibrating Arm/ Weights DAQ/ LabVIEW

26. Exp #1 Calculations Coefficient of Lift: Coefficient of Drag: Reynolds Number: CL: Coefficient of Lift CD: Coefficient of Drag Rec: Reynolds Number L: Lift Force D: Drag Force ρ: Free stream density U: Free stream velocity S: Surface area 𝜇: Viscosity c: Plate with Theoretical value of the CL and CD of a flat plat at O° Angle of Attack and Re of 10,000 [Ref 7]:

27. Electronics • 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 `

30. Current system VOLTAGE 0 to 1000VDC, POWER 20W ULTRAVOLT High Voltage Power Supply Item number: 180293665388 FREQUENCY DC supply. Needs AC/AD converter Cannot be lower than 1Khz = Residual Current $100.00 + Shipping and Tax Reference [12]: www.ultravolt.com ;

31. References • SUBSONIC PLASMA AERODYNAMICS USING LORENTZIAN MOMENTUM TRANSFER IN ATMOSPHERIC NORMAL GLOW DISCHARGE PLASMAS - J. Reece Roth(jrr@utk.edu), Hojung Sin (hsin@utk.edu)and Raja Chandra Mohan Madhan - UT Plasma Sciences Laboratory • 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 • Google Images • Flow control in low pressure turbine blades using plasma actuators - - Karthik Ramakumar, Arvind Santhanakrishnan, Jamey Jacob - University of Kentucky • Flow Control And Lift Enhancement Using Plasma Actuators - Karthik Ramakumar and Jamey D. Jacob†- AIAA-2005-4635 - Fig 13 • PIFAS Team • 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. • http://en.wikipedia.org/wiki/Electrical_resistivity • http://www.aoe.vt.edu/~mason/Mason_f/A380Hosder.pdf • http://www.kaptontape.com/tech_pages/1mil_polyimide_sheets.php • http://www.pstc.org/papers/pdfs/McAlees.pdf • http://www.ultravolt.com

32. 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 visit http://www.my.fit.edu/eflow