Modeling of Plasma Flow Control Over a High-Speed Delta Wing

Abstract

†‡ Numerical modeling of vortex flow over a delta wing with sharp leading edges of 60 ο sweep angle has been performed at free-stream Mach number 1.5 and angles of attack from 0 ο to 30 ο . The flow field contains two strong vortices generated by the rollup of the shear layer emanating from the wing leading edges. Large radial and axial velocities of these primary vortices reduce pressure on the leeside wing surface that may affect the wing aerodynamic performance. Numerical solutions of 3-D Navier-Stokes equations are consistent with available experimental and numerical data. Detailed parametric study has been performed to estimate feasibility of the vortex flow control using the surface barrier discharge (SBD) actuators: the wing-apex SBD, the leading-edge SBD and the multi-element SBD. Heat and momentum forcing produced by these actuators is modeled by analytical approximations of volumetric force and heat distributions. It was shown that the vortex breakdown locus can be controlled by the aforementioned SBD actuators. However this weakly affects the integral aerodynamic forces (lift and drag). Numerical simulations of unsteady flow field indicate that the vortex breakdown evolves with time. This unsteady behavior is sensitive to the SBD forcing. Nevertheless, appreciable migrations of the vortex burst produce small effect on the lift coefficient.