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)