A numerical method (inverse method) was developed for a gas-particle supersonic flow past two-dimensional blunt bodies. This method is based on two transformations (von Mises and additional one), which are convenient for determining the shock layer flow field and the body shape. Using the present method, the pure gas flow field around a circular cylinder was first solved numerically for freestream Mach numbers M_∞=3.0, with particle diameter dp=2, 5, 10μm and freestream loading ratios αα=0, 0.2, 0.5 and 1.0, respectively. The effects of dp and α on the shock stand-off distance, the body surface pressure and flow quantities along the stagnation streamline are discussed, and flow patterns in the shock layers are shown.