Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators

Abstract

The effect of magnetohydrodynamic (MHD) plasma actuators on the control of hypersonic shock wave/turbulent boundary layer interactions is investigated here using Reynolds-averaged Navier-Stokes calculations with low magnetic Reynolds number approximation. A Mach 5 oblique shock/turbulent boundary layer interaction was adopted as the basic configuration in this numerical study in order to assess the effects of flow control using different combinations of magnetic field and plasma. Results show that just the thermal effect of plasma under experimental actuator parameters has no significant impact on the flow field and can therefore be neglected. On the basis of the relative position of control area and separation point, MHD control can be divided into four types and so effects and mechanisms might be different. Amongst these, D-type control leads to the largest reduction in separation length using magnetically-accelerated plasma inside an isobaric dead-air region. A novel parameter for predicting the shock wave/turbulent boundary layer interaction control based on Lorentz force acceleration is then proposed and the controllability of MHD plasma actuators under different MHD interaction parameters is studied. The results of this study will be insightful for the further design of MHD control in hypersonic vehicle inlets.

Numerical Investigation of the Hypersonic Inlet under Throttling with Heat Source

“…SWBLI generates boundary layer thickening, separation of bubbles/regions, and increased turbulence effects, all of which slow down total the pressure recovery. Several techniques have been employed to reduce the negative effects of SWBLI [4][5][6][7].…”

“…According to current computational calculations, lasers may result in drag reduction, positive adjustment of the aerodynamic forces, and shock control [20]. Jiang et al, [7] numerically investigated the effect of the MHD plasma actuator's location on the SWBLI and classified them into four categories based on the distinct processes. They discovered that placing the actuator in the isobaric zone had the biggest impact on minimizing the divergence distances.…”

Numerical study of lateral coolant jet on heat reduction over nose cone with double-aerodome at hypersonic flow

“…The flow analyses of the hypersonic vehicles are widely done to disclose the effective factors and parameters associated with aerodynamic heating [13][14][15][16] . Although these studies have presented significant data about the mechanism of the aerodynamic heating around the nose of the cone, there are still some challenges i.e.…”

Mixing and combustion in supersonic/hypersonic flows

“…3 shows a schematic diagram of the mechanism of shock train self-excited oscillation in the isolator (Hou et al, 2020). Jiang et al (2020) studied the hypersonic shock wave/turbulent boundary layer interaction control induced by magnetohydrodynamic (MHD) plasma actuators. A novel parameter based on Lorentz force acceleration is proposed to predict control efficiency.…”