Active Control of Subsonic Cavity Flow Using Plasma Actuators

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Title: Active Control of Subsonic Cavity Flow Using Plasma Actuators
Creators: Kamps, Nathan G.
Advisor: Samimy, Mo
Issue Date: 2007-06
Abstract: Due to the prevalence of stealth technology on increasing numbers of new aircraft, weapons and electronics that had previously been stored under the aircraft wings are now being stored in weapons bays inside the fuselage. When these bays are opened however, a damaging flow situation can arise to create high amplitude pressure fluctuations capable of damaging structures and systems of the aircraft and the weapons stored in the bay. Thus a major area of research at the Gas Dynamics and Turbulence Laboratory (GDTL) has been focused on the suppression of these pressure fluctuations. Previous results using active flow control and a compression driver showed good flow authority up to Mach 0.40, when actuator effectiveness was lost. Other research at the GDTL has focused on the use of localized arc filament plasma actuators (LAFPA’s) to control flow instabilities in a high Mach number free jet. The focus of this research was to incorporate the plasma actuators in a cavity flow facility and investigate their effectiveness at suppressing the tone generated by flows of higher Mach numbers. The results presented in this paper detail the results of testing several different actuator configurations on Mach 0.69 flow over a shallow cavity. Advisor: Mo Samimy
Embargo: No embargo
Series/Report no.: The Ohio State University. Department of Mechanical Engineering Honors Theses; 2007
Keywords: cavity flow
plasma actuator
Rossiter modes
sound pressure level
cavity acoustic
active flow control
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Attribution-NonCommercial-NoDerivs 3.0 Unported This item is licensed under a Creative Commons License:
Attribution-NonCommercial-NoDerivs 3.0 Unported