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Delta-Wing Vortex Lift Enhancement Using Oblique Channel Distribution
Advisor: Dr. McClain Project Manager: Meag McNaryRuben Nunez
Adam EakerRyan Parker
Drew Waggoner
ME LAB 4335- Final Presentation
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OverviewInitial ObjectiveFinal ObjectiveTheoryExperimentationSchedule SummaryResultsSignificanceSummaryRecommendationsQuestions
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Initial ObjectiveQuantify the steady flow effects of oblique
element distributions interacting with vortical structures attached to a delta wing micro unmanned air vehicle
Areas of interest:High angle of attackRoughness elementsLift and Drag
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Final ObjectiveQuantify the steady flow effects of obliquely
aligned channels interacting with vortical structures on a delta wing micro unmanned air vehicle
Areas of interest:High angles of attackLow Reynolds Numbers Obliquely aligned channelsLift and Drag
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Theory – Delta Wing
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Theory – Vortex BehaviorUnpredictable behavior
Leading-edge vortices Induces additional lift by pressure decrease
on suction surface
Vortex breakdown Vortex expands into highly fluctuating structure Induced by high angles of attack or pressure rise Vortex separates from wing Disadvantages:
Wing fluttering Loss of performance Decrease in lift
Vortex Breakdown
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Delay bursting of vorticesIncreases performance
Controlled by increasing ωθ and induce secondary flow
Methods:Mechanical
Local action by contouring surfacePneumatic
Introduce perturbations through air flow
Theory – Vortex Breakdown Control
Obliquely aligned elements
Vθ
VL
Leading-edge separation line
Vortex separation line reattachment line
Control elementregion
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Jet FlapsLeading or Trailing edge
Can be difficult to implement.
Leading edge: + large increase on lift,- large increase on drag.
Trailing edge:+ increase stability - small increase on lift,
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Piezoelectric StripsBonded on delta wing for
active control of oscillations.
Serve as sensors and actuators.
Voltages applied across strips create forces to counter oscillations.
Lightweight, cheap, and easy to manufacture.
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Obliquely Aligned ElementsElements prevent
breakdown of vortices by directing air flow and produce high lift forces.
Elements also prevent buffeting and oscillations.
Moderate drag penalty.
Leading-edge separation line
Vortex separation line reattachment line
Control elementregion
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Obliquely Aligned ChannelsDesigned to stabilize
the vortical flow.
Restrict pressure rises that precipitate breakdown.
Increase ωθ and induce secondary flow
Promote Reattatchment
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ExperimentationSet up to determine the lift and drag coefficients on
a Delta Wing with varying angles of attackMeasurements:
Data Acquisition LABVIEW
Angle of Attack (0° to 45°) Using a set screw to adjust attack angle in 5° increments
Lift and Drag Force Force Balance
Static Pressure Difference Using a Pitot-Static Tube and
the PCL2A
Delta Wing
Wind Direction
Test Section
WIND TUNNEL
Figure 1: Wind tunnel experiment set-up to determine lift and drag coefficients on a Delta Wing with a fixed wind velocity.
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Initial Schedule Summary
Preliminary Data Collection
Test Plan Due
Develop Connector Piece
Develop Rotating Mechanism
Printing of Delta Wings
Data Collection
Final Presentation
Final Project Due
2/6/20
11
2/16/2
011
2/26/2
011
3/8/20
11
3/18/2
011
3/28/2
011
4/7/20
11
4/17/2
011
4/27/2
011
5/7/20
11
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Final Schedule Summary Preliminary Data Collection
Research
Test Plan Due
Work on Report
Develop Connector Piece
Develop Rotating Mechanism
Manufacturing of Delta Wings
Data Collection
Final Presentation
Final Project Due
6-Feb 16-Feb 26-Feb 8-Mar 18-Mar 28-Mar 7-Apr 17-Apr 27-Apr 7-May
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Results
0 5 10 15 20 25 30 35 40 45 500.00
0.20
0.40
0.60
0.80
1.00
1.20
1.40
1.60
Coefficients of Lift and DragRe=179,260 V=15.09m/s
Smooth CLSmooth CDChanneled CLChanneled CD
Angle of Attack (deg)
Coeff
icie
nts
of L
ift
and
Dra
g
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Results
0 5 10 15 20 25 30 35 40 45 500
1
2
3
4
5
6
7
8
9
Lift/DragRe=179,260 V=15.09m/s
SmoothChanneled
Angle Of Attack
L/D
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ResultsOverall trend is the same for both wings
Lift and drag are less in the channeledIncreased difference in lift just before stall
Stall occurred at approximately 35°Lift after stall was greater for the channeled
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SignificanceOblique channels do not increase
performanceThe effects after stall might suggest
improvement is possible
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SummaryThere are multiple ways to manipulate the
vortical breakdownMechanicalPneumatic
Channeled wing does not drastically increase performanceLift force reducedDrag force reduced
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RecommendationsImprovements in the channeled design might
allow for better performance than current model
Test at higher Reynolds numbersResume original test criteria
Oblique elemental distributions
Arrangement of the distributions
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Questions?