Abstract
This paper describes a study of the causes of the inaccuracies in the evaluation of airloads by application of the Mach box numerical scheme. A refinement to lessen inaccuracies in the evaluation of steady /unsteady supersonic airloads is presented. The refinement is based on the aerodynamic influence coefficient (AIC) partition scheme and application of conical flow concept in the small perturbation flowfield. The refinement is intended to minimize the nonconverging error due to irregular points. Care is taken to retain the computational efficiency of the basic Mach box scheme. The new method is demonstrated for both planar and nonplanar interaction cases and is shown to result in smoother, more realistic pressure distributions.
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