Mathematical Fluid Dynamic Modeling of Plasma Stall-spin Departure Control

This report summarizes theoretical and CFD studies related to surface discharge to quench stall-slip departure due to asymmetric vortex shedding on aircraft nose tips, augment directional control/authority agility, and develop tailless capability. This approach offers adaptability in rapidly changing flight and mission conditions, constructional simplicity, massless operation, no changes in aerodynamic shape, no influence on aircraft characteristics when the system is not in use, and low weight and power penalties, and closed loop feedback control. In the first phase of the effort, lower-order theoretical modeling showed that vortex symmetry breakdown strongly depends on the boundary-layer separation locus. The latter can be effectively controlled by a surface discharge located upstream from the separation line. Using spark discharges of relatively small power (less than 1 kW) it is feasible to shift the separation line toward the windward surface and suppress vortex asymmetry.