boeing - st.louis march 7, 2006 plasma actuators for landing gear noise control* f. o. thomas, a....
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![Page 1: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/1.jpg)
Boeing - St.LouisMarch 7, 2006
Plasma Actuators for Landing Gear
Noise Control*
F. O. Thomas, A. Kozlov, T.C. Corke
* Supported by NASA Langley NAG1-03076
AIAA -2005-3010 Presented at 11th AIAA / CEAS Aeroacoustics Conference,
May 25, 2005.
Langley Research Center
![Page 2: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/2.jpg)
Boeing - St.LouisMarch 7, 2006
radiated noise
radiated noise
U
plasma actuators on
plasma actuatorsplasma actuators
U
no actuation
The Plasma Fairing Concept
![Page 3: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/3.jpg)
Boeing - St.LouisMarch 7, 2006
Cylinder Model Utilizing Four Actuators
1. Quartz cylinder wall forms adielectric barrier: ( thickness of 2.5 mm)
2. Copper foil electrode (6.4 mm)
3. Encapsulated electrode:lead foil (25.4 mm)
1. Inner insulation (7 layers of 0.005” thick Kapton tape)
5. Regions of plasma formation
• Sinusoidal A.C. voltage is applied at 8.1 kV rms and f = 10 kHz.
![Page 4: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/4.jpg)
Boeing - St.LouisMarch 7, 2006
Cylinder Model Utilizing Four Actuators
![Page 5: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/5.jpg)
Boeing - St.LouisMarch 7, 2006
Single Actuator-Induced Mean Velocity Field
Plasma actuator
No external flow
Plasma-inducedCoanda effect
![Page 6: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/6.jpg)
Boeing - St.LouisMarch 7, 2006
Dual Actuator-Induced Mean Velocity
No external flow
Plasma actuators
![Page 7: Boeing - St.Louis March 7, 2006 Plasma Actuators for Landing Gear Noise Control* F. O. Thomas, A. Kozlov, T.C. Corke * Supported by NASA Langley NAG1-03076](https://reader033.vdocuments.us/reader033/viewer/2022051622/56649d415503460f94a1cb3a/html5/thumbnails/7.jpg)
Boeing - St.LouisMarch 7, 2006
Steady Actuation : ReD = 30,000
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Boeing - St.LouisMarch 7, 2006
Wake Velocity Auto-spectra (ReD = 30,000)
1x10
-3
1x10
-2
1x10
-1
1x10
0
1x10
1
1x10
2
1x10
3
1x10
0
1x10
1
1x10
2
1x10
3
FREQUENCY (Hz)
PLASMA OFF
STEADY PLASMA
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Boeing - St.LouisMarch 7, 2006
ReD=30,000Unsteady Actuation: 48 Hz (StD=1)
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Boeing - St.LouisMarch 7, 2006
ReD=30,000Vorticity Unsteady Actuation: 6Hz
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Boeing - St.LouisMarch 7, 2006
Unsteady Symmetric Actuation: ReD = 30,00048 Hz., 25% Duty Cycle: Vorticity
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Boeing - St.LouisMarch 7, 2006
Unsteady Symmetric Actuation: ReD = 30,00025% Duty Cycle,
f =48 Hz (StD=1)