The influence of steady energy addition into the flow by a low-voltage DC-arc discharge located upstream of conically nosed and spherically blunted bodies was investigated experimentally in the Ludwieg-Tube Facility at Mach 5. The results include drag force measurements and shadowgraph flow visualizations. The flow-field structure, arising due to the bow-shock/heated-wake interaction, as well as the bow-shock intensity and heating power effects on the drag reduction is analyzed in this paper. The results demonstrate the existence of an optimum heating rate, providing a maximum effectiveness of energy addition and showing distinct drag reductions up to 70% dependent on test conditions and model geometries.

Effects of steady flow heating by arc discharge upstream of non-slender bodies

The interactions between supersonic streamwise vortices and oblique shock waves are theoretically and numerically investigated by three-dimensional (3D) Navier-Stokes equations. Based on the two inequalities, a criterion for shock-induced breakdown of the streamwise vortex is proposed. The simple breakdown condition depends on the Mach number, the swirl number, the velocity deficit, and the shock angle. According to the proposed criterion, the breakdown region expands as the Mach number increases. In numerical simulations, vortex breakdown appeared under conditions of multiple pressure increases and the helicity disappeared behind the oblique shock wave along the line of the vortex center. The numerical results are consistent with the predicted breakdown condition at Mach numbers 2.0 and 3.0. This study also found that the axial velocity deficit is important for classifying the breakdown configuration.

Criterion for vortex breakdown on shock wave and streamwise vortex interactions.

https://uwe-repository.worktribe.com/preview/924694/1-s2.0-S1000936116300188-main.pdf

Large-eddy simulation of shock-wave/turbulent boundary layer interaction with and without SparkJet control

Numerical investigation of oblique shock wave/vortex interaction

Keywords: Flow Control ; Turbomachinery ; Surface DBD ; weakly ionized Plasma ; transonic flow ; shock-boundary layer interaction ; surface dielectric barrier discharge ; GTT ; LTT Reference LTT-CONF-2009-001 Record created on 2009-01-23, modified on 2016-08-08

Effects of a surface dielectric barrier discharge on transonic flows around an airfoil

Three-dimensional unsteady Euler simulations are presented for the interaction of a streamwise vortex with an oblique shock of angle β = 23.3° at Mach 3 and 5. The flowfield features are analyzed for weak, moderate and strong interaction regimes. The details of the free recirculation zone at conditions of subsonic and supersonic flow on the vortex axis are considered. The vortex breakdown under conditions of a subsonic vortex core is characterized by a continuous growth and gradual degeneration of the region, unlike the supersonic core condition wherein a steady recirculation zone is achieved. The possibility of using a localized steady and pulsed periodic energy deposition on the vortex axis for stimulating the breakdown is demonstrated for various interaction regimes. It is shown that the formation of a subsonic wake downstream of an energy source lying on the vortex axis contributes to a more significant growth of the dimensions of the recirculation zone compared to the case when the vortex core remains supersonic. The possibility of achieving the effects similar to the steady case is demonstrated by the effect of a pulsed periodic energy source on the flow under consideration for corresponding equivalence parameters.

E. A. Pimonov

Papers

Numerical modeling of vortex/shock wave interaction and its transformation by localized energy deposition