The flow characteristics of asymmetric vortices and the side force of a slender body flight vehicle with chine nose at high angles of attack have been studied using a three-dimensional upwind Navier–Stokes method with the k– ω turbulence model and a simple laminar–turbulent transition model. Asymmetrically changing turbulent viscosities that arise from asymmetric laminar–turbulent transition conditions cause asymmetric cross-flow vortex structures and side forces at higher angles of attack. However, certain type of edges may cause fixed flow separations on these edges. In this study, the chine nose shape with chine edge on its both sides is considered for the method to reduce side force. The asymmetric flow control capacity of chine nose shapes at high angles of attack is studied.