Self-indused roll-oscillation delta wing on high angeles of attack

The self - induced roll oscillations (wing rock) are studies by mean of numerical simulations of a separated flow an around of delta wing. A computational algorithm is constructed on the basis of the vortex-lattice method. For regimes of self-induced vibrations, the calculation results agree well with experimental data. The vortex nature and the mechanism of self-induced oscillations are studied. Initial phase of self-induced oscillations, integral curves of motion equation on the phase plane, vortex structure above a delta wing are considered. The self - induced roll oscillations of delta wing are being considered to apply in car industry as an aerodynamic windshield cleaner on a high speed move.