flow control over sharp-edged wings josé m. rullán, jason gibbs, pavlos vlachos, demetri telionis...
TRANSCRIPT
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Flow Control over Sharp-Edged Wings
José M. Rullán, Jason Gibbs, Pavlos Vlachos, Demetri Telionis
Dept. of Engineering Science and Mechanics
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Flow Control Team
P. Vlachos J. Rullan J. Gibbs
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Overview Background Facilities and models Experimental tools (PIV, pressure scanners, 7-hole probes)
Results:1. Aerodynamics of swept wings2. Flow Control at high alpha3. CONTROL SEPARATED FLOW
(NOT SEPARATION)4. 10 4 < Re < 10 6
Conclusions
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Background
Diamond-Planform, sharp-edged wings common on today’s fighter aircraft.
Little understanding of aerodynamic effects at sweeping angles between 30° and 40° AOA.
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Vorticity Rolling over Swept Leading Edges
Sweep> 500 Sweep~450
Sweep~400 Sweep~400
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Background (cont.) Low-sweep wings stall like *unswept wings or *delta wings
Dual vortex structures observed over a wing swept by 50 degrees at Re=2.6X104 (From
Gordnier and Visbal 2005)
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Yaniktepe and Rockwell
Sweep angle 38.7º for triangular planform Flow appears to be
dominated by delta wing vortices
Interrogation only at planes normal to flow
Low Re number~10000 Control by small
oscillations of entire wing
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Facilities and models
VA Tech Stability Wind Tunnel
U∞=40-60 m/s Re≈1,200,000
44” span diamond-planform wing
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Facilities and models
Water Tunnel with U∞=0.25 m/s Re≈30000
CCD camera synchronized with Nd:YAG pulsing laser
Actuating at shedding frequency
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Wind Tunnel Model
Model is hollow.
Leading edge slot for pulsing jet
8” span diamond wing
Flow control supplied at inboard half of wing
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Facilities and models(cont.)
planes z/c z/b
1 0.068 0.092
2 0.156 0.209
3 0.249 0.334
4 0.340 0.456
5 0.417 0.559
6 0.467 0.626
7 0.531 0.711
8 0.581 0.778
9 0.644 0.863
10 0.694 0.930
planes x/c
A 0.28
B 0.513
C 0.746
D 1.086
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Data acquisition with enhanced time and space resolution ( > 1000 fps)Image Pre-Processing and Enhancement to Increase signal qualityVelocity Evaluation Methodology with accuracy better than 0.05 pixels and space resolution in the order of 4 pixels
Sneak Preview of Our DPIV System
Time-Resolved DPIV
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DPIV Digital Particle Image Velocimetry System
III Conventional Stereo-DPIV system with: 30 Hz repetition rate (< 30 Hz) 50 mJ/pulse
dual-head laser 2 1Kx1K pixel cameras
Time-Resolved Digital Particle Image Velocimetry System I An ACL 45 copper-vapor laser with 55W and
3-30KHz pulsing rate and output power from 5-10mJ/pulse
Two Phantom-IV digital cameras that deliver up to 30,000 fps with adjustable resolution while with the maximum resolution of 512x512 the sampling rate is 1000 frme/sec
Time-Resolved Digital Particle Image Velocimetry System II : A 50W 0-30kHz 2-25mJ/pulse Nd:Yag Three IDT v. 4.0 cameras with 1280x1024
pixels resolution and 1-10kHz sampling rate kHz frame-straddling (double-pulsing) with as little as 1 msec between pulses
Under Development: Time Resolved Stereo DPIV with Dual-head
laser 0-30kHz 50mJ/pulse 2 1600x1200 time resolved cameras …with build-in 4th generation intensifiers
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Actuation Time instants of pulsed jet(a)
(b)
(c)
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PIV Results Velocity vectors and vorticity contours
along Plane D
no control control
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PIV results (cont.) Planes 2(z/b= 0.209) and 3
(z/b= 0.334) with actuation.
Plane 2 Plane 3
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Results (cont.) Plane A, control, t=0,t=T/8
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Results (cont.) Plane A, control, t=2T/8,t=3T/8
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Results (cont.) Plane A, control, t=4T/8,t=5T/8
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Results (cont.) Plane A, control, t=6T/8,t=7T/8
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Results (cont.) Plane 8, t=0
No control Control
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Results (cont.) Plane 8, t=T/8
No control Control
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Results (cont.) Plane 8, t=2T/8
No control Control
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Results (cont.) Plane 8, t=3T/8
No control Control
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Results (cont.) Plane 8, t=4T/8
No control Control
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Results (cont.) Plane 8, t=5T/8
No control Control
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Results (cont.) Plane 8, t=6T/8
No control Control
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Results (cont.) Plane 8, t=7T/8
No control Control
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Results (cont.) Plane 9, t=0
No control Control
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Results (cont.) Plane 9, t=T/8
No control Control
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Results (cont.) Plane 9, t=2T/8
No control Control
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Results (cont.) Planes B and C, control
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Results (cont.) Plane D, no control and control
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Flow animation for Treft planes
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Circulation variation over one cycle
Plane A Plane B
Plane B
Plane A
Plane C
Plane D
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Circulation Variation (cont.)
Plane C Plane D
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Pressure ports location
Spanwise blowing nozzles
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ESM Pressure profiles @ 13 AOA for Station 3
Half flap Full flap
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ESM Pressure profiles @ 13 AOA for Station 4
Half flap Full flap
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ESM Pressure profiles @ 13 AOA for Station 5
Half flap Full flap
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ESM Pressure profiles @ 13 AOA for Station C
Half flap Full flap
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Pressure distributions for α=130.
Stations 5-7 Stations 8-10
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Pressure distributions for α=170.
Stations 5-7 Stations 8-10
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ConclusionsWITH ACTUATION: Dual vortical patterns are activated and
periodically emerge downstream Vortical patterns are managed over the wing Suction increases with control Oscillating mini-flaps and pulsed jets equally
effective Flow is better organized Steady point spanwise blowing has potential
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Future Work Study effect of sweep with new model Explore the frequency domain Identify local “3-D actuators” to
control these 3-D flow fields Aim at controlling forces and
moments