Abstract: To guide the design of two-dimensional hypersonic inlet surface, boundary layer parameters had been calculated using high precision CFD method for two types of two-dimensional hypersonic blunt wedges. The effects of leading edge radius, wall temperature and pressure gradient on boundary layer parameters had been analyzed. The streamwise variation of displacement thickness, total pressure recovery and pressure gradient had been obtained. The research show that leading edge radius and wall temperature affect boundary layer parameters significantly, if fix them, reverse pressure gradient will decelerate the increasing rate of boundary layer, while favorable pressure gradient accelerate the increasing of boundary layer.