1. F P I A S LASMA NDUCED LOW ERODYNAMIC TRUCTURE http://my.fit.edu/eflow/ Disclosure: Figures do not have appropriate references; presentation under construction

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. Design Airfoil with plasma actuators in place. 1.07 mm trip wire located at the leading edge (not visible).

5. Picture 1: NACA 0015 at an AOA of 12°, plasma actuators off – Flow separation/Near Critical AOA

6. Picture 2: NACA 0015 at an AOA of 12°, electrode voltage V = 3.6 kV @ 4.2 kHz – Flow separation is delayed, causing significant reductions in drag

7. 1% reduced drag Boeing 727 = 20,000 gallons of fuel per year = OVER $100,000.00 savings/airplane

8. Updated in MS project

9. 2 – DUGO DF102-P01 Flyback Transformer Current Progress Implementation of microprocessor based control of plasma panels: (ex: 16 bit PIC Microcontroller) frequency # and location of panels operating Communication between HV systems One test model with several scenarios Up to 30K Volts on each Fyyback operating independent systems

10. FREQUENCY Optimal : 5Khz (literature) Our Future Tests: 2,4,5,6 Khz Cannot be lower than 1Khz = Residual Current VOLTAGE Optimal :30kV Our Performed Tests: 1,3,4,5,10kV 30 kV and other test dependent on equipment availability Cannot be lower than 1Khz : Residual Current = periodicity loss TEMPERATURE Literature experiments: High Thermal 10 7 K Low Thermal 2*10 4 K non Thermal (surfaces) = 300K Currently we are calculating our own

11. Current Design Overview

12. HIGH VOLTAGE GENERATOR PLASMA ARC IN EXPERIMENTAL SETUP POWER SUPPLY Transformer Heat Sink Potenciometer Capacitor LM555 MOSFET Driver Work

13. High Voltage Generation Variable Voltage, 120V – 50KV AC Current Power source, 1V DC – 60V DC Considerations High voltage cables Operation/Maintenance Safety Size and Weight Battery Storage (Series) Permanent Generation (Turbines) Efficiency ratio Takeoff cycle Landing cycle

14. 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

15. END For more information please visit http:// www.my.fit.edu/eflow