f p i a s lasma nduced low erodynamic tructure
TRANSCRIPT
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