Shock-fitting solution of the supersonic flowfield in a rounded internal corner

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The conical inviscid supersonic flowfield in a rounded internal corner was investigated numerically. A number of comparisons were made with previously obtained sharp corner solutions, and an experiment was conducted to provide a rounded corner comparison. The experimental investigation included mapping of the shock wave and contact surface locations at a Mach number of 4.1 for a model with unequal wedge angles and a conical!) rounded corner. There is little pressure change across the three-dimensional flowfield with a sharp corner. As the amount of corner rounding is increased, the pressure gradient toward the corner increases, and pockets of increased pressure appear at the ends of the rounded section. Increasing the freestream Mach number changes the relative shock-wave shapes. The solution was successfully executed over a range of Mach numbers from 2 to 6 and over a range of wedge angles from 4 to 18 deg.