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.

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Presentation transcript:

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 NAG AIAA Presented at 11th AIAA / CEAS Aeroacoustics Conference, May 25, Langley Research Center

Boeing - St.Louis March 7, 2006 The Plasma Fairing Concept

Boeing - St.Louis March 7, 2006 Cylinder Model Utilizing Four Actuators 1.Quartz cylinder wall forms a dielectric 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.

Boeing - St.Louis March 7, 2006 Cylinder Model Utilizing Four Actuators

Boeing - St.Louis March 7, 2006 Single Actuator-Induced Mean Velocity Field Plasma actuator No external flow Plasma-induced Coanda effect

Boeing - St.Louis March 7, 2006 Dual Actuator-Induced Mean Velocity No external flow Plasma actuators

Boeing - St.Louis March 7, 2006 Steady Actuation : Re D = 30,000

Boeing - St.Louis March 7, 2006 Wake Velocity Auto-spectra (Re D = 30,000)

Boeing - St.Louis March 7, 2006 Re D =30,000 Unsteady Actuation: 48 Hz (St D =1)‏

Boeing - St.Louis March 7, 2006 ReD=30,000 Vorticity Unsteady Actuation: 6Hz

Boeing - St.Louis March 7, 2006 Unsteady Symmetric Actuation: Re D = 30, Hz., 25% Duty Cycle: Vorticity

Boeing - St.Louis March 7, 2006 Unsteady Symmetric Actuation: Re D = 30,000 25% Duty Cycle, f =48 Hz (St D =1)‏