Three-dimensional shock wave reflections from a cone with angles of attack were examined experimentally and numerically. The Mach number of the incident shock wave was 1.35. The attack angles of a cone model with a semi-apex angle of 30° were 10° , 15° , 20° and 25°. The experiments were performed using a vertical shock tube, and the wave configurations were visualized using a conventional schlieren system. Numerical simulations of the shock wave reflections were also conducted using unstructured solution adaptive grids. The triple-point distributions around the cone were reconstructed from the visualized wave configurations, and then compared with those obtained from the numerical simulations. The characteristic flow fields behind a curved Mach stem around the cone are revealed.
