Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator

• Published in: Physics of fluids (1994) 2012-07, Vol.24 (7)
• Main Authors: NARAYANASWAMY, Venkateswaran, RAJA, Laxminarayan L, CLEMENS, Noel T
• Format: Article
• Language: English
• Subjects: Actuators; Amplitudes; Boundary layer and shear turbulence; Boundary layer interaction; Boundary layer thickness; Compressible flows; shock and detonation phenomena; Exact sciences and technology; Flow control; Fluid dynamics; Fundamental areas of phenomenology (including applications); Physics; Separation; Shock waves; Shock-wave interactions and shock effects; Turbulent flows, convection, and heat transfer; Unsteady; Upstream
• ISSN: 1070-6631; 1089-7666
• DOI: 10.1063/1.4731292

A pulsed-plasma jet actuator is used to control the unsteady motion of the separation shock of a shock wave/boundary layer interaction formed by a compression ramp in a Mach 3 flow. The actuator is based on a plasma-generated synthetic jet and is configured as an array of three jets that can be injected normal to the cross-flow, pitched, or pitched and skewed. The typical peak jet exit velocity of the actuators is about 300 m/s and the pulsing frequencies are a few kilohertz. A study of the interaction between the pulsed-plasma jets and the shock/boundary layer interaction was performed in a time-resolved manner using 10 kHz schlieren imaging. When the actuator, pulsed at StL approximately 0.04 (f = 2 kHz), was injected into the upstream boundary layer, the separation shock responded to the plasma jet by executing a rapid upstream motion followed by a gradual downstream recovery motion. Schlieren movies of the interaction showed that the separation shock unsteadiness was locked to the pulsing frequency of the actuator, with amplitude of about one boundary layer thickness. Wall-pressure measurements made under the intermittent region showed about a 30% decrease in the overall magnitude of the pressure fluctuations in the low-frequency band associated with unsteady large-scale motion of the separated flow. Furthermore, by increasing the pulsing frequency to 3.3 kHz, the amplitude of the separation shock oscillation was reduced to less than half the boundary layer thickness. Investigation into the effect of the actuator location on the shock wave/boundary layer interaction (SWBLI) showed qualitatively and quantitatively that the actuator placed upstream of the separation shock caused significant modification to the SWBLI unsteadiness, whereas injection from inside the separation bubble did not cause a noticeable effect.