1. P I F A S LASMA NDUCED LOW ERODYNAMIC TRUCTURE
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.
As you know, our goal is to create an aerodynamic structure that will outperform current designs of wings with the use of plasma actuators

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
According to values found from past research and publications, we developed a set of metrics for project success.

4. 1% reduced drag Boeing 727 = 20,000 gallons of fuel
Exposed vs Grounded Electrodes
Dual dielectric layer (protejer airfoil) / material
Plasma region (gap)
Electrode diameter ratio and material
Construction
[Ref. 2]
1% reduced drag Boeing 727 = 20,000 gallons of fuel
per year = OVER $100, savings/airplane

5. Project Approach Literature review Calculations Experimentation Design
Construction
Optimization
In order to successfully attain our project goal and objectives, we followed a simple step by step approach consisting of ….

6. Project Approach Literature review Collect published research papers
Extract fundamental information
Characterize system
Develop theory
PIFAS team has collected over 30 technical references and publications from universities including Notre Dame, Tennessee, Stanford, and AIAA. over the past months. From this, we have been able to extract information on the overall system behavior of plasma actuators as shown earlier and to

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. A Gantt chart was created in order to set a timeline for the team to follow and stay on schedule. As you can see, we are currently near the completion of the lit. review and concentrating on the experimentation, more specifically FIT wind tunnel test using a force balance, which will be discussed in more detail in the following section. For this, we developed a set of metrics and specifications for our goal completion.
Current Date

14. Design Specifications
Design specs
Design Specifications
Metrics
Units
Value
Dielectric Material
High Dielectric Constant -
3.5
Resistivity
Ohms
> 10,000
Width of the Structure Test Piece
Wind Tunnel Width (UCF vs. FIT) m
< (21) 
Length of the Structure Test Piece
Wind Tunnel Length (UCF vs. FIT)
> 1 
Shape of airfoil (NACA profile)
Large Curvature
NACA 0015 
Uniform Ionization of air
Variable Frequency Range Hz
Actuator Width mm
5  
Voltage Range V
Electric Field Strength
V/m
Actuator Shape
Ionization Effects
Actuator Material
Conductivity
μS/m
59.6
Optimal Plasma Profile
Actuator Gap Width
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

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. Chord wise Position (y/c)*
Force balance method
Actuator configuration
Multiple 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
OFF ON 2
0.465 3
0.93
* Chord length c = 9 in

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 Flat Plate with actuators (Top view)
Copper foil anode 2
Copper foil cathode
Flat Plate with actuators (Top view)

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

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

25. Experiment #1 setup Test Section (21” x 21”) Calibrating Arm/ Weights
Florida Tech Low-Speed Wind Tunnel [Ref: 6]
Calibrating Arm/ Weights
Force Balance of Wind Tunnel [Ref: 6]
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]: CL CD
Numerical
0.036
Experimental
0.022 ± 1.98 × 10−4
0.041 ± 1.07 × 10−3

27. Implementation on airfoil /aircraft
Electronics DC
Lethal power levels
Corona Discharge AC
Safe power levels
Arc Discharge
Implementation on airfoil /aircraft
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 `

28. Final Circuit
Frequency and Voltage
1 -10Khz
1- 15KV
Power Losses
Dielectric Heating
Impedance Matching
Weight & Size
Implement on existing airplanes
Transport to testing facilities
Heat Produced
Burn of actuator
Damage to experimenters or vehicle
Electrical Conductivity
Choice of dielectric
Insulation of power system

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

31. References
SUBSONIC PLASMA AERODYNAMICS USING LORENTZIAN MOMENTUM TRANSFER IN ATMOSPHERIC NORMAL GLOW DISCHARGE PLASMAS - J. Reece Hojung Sin Raja Chandra Mohan Madhan - UT Plasma Sciences Laboratory
PIFAS Team 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 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.

32. Group Members For more information please visit
Gonzalo Barrera
Esteban Contreras
Joseph Dixon
Andres Fung
Sumit Gupta
Georgio mahmood
Ivan Mravlag
Christian O. Rodriguez
Septinus Saa
For more information please visit