Abstract
A first-order method for predicting three-dimensional steady flow past aerodynamic shapes is described. Finitedifference equations which smooth real shock discontinuities are derived from a semicharacteri stic representation of equations of motion in a nonconservation law form such that stream surfaces form two families of coordinate surfaces. Accurate boundary conditions are applied systematically. Numerical results for a faired wedge, an axisymmetric body and a simple delta wing with sharp supersonic leading edges show that the nonconservation law method has good over-all performance.
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