Abstract
as our present one is just those truncation errors which are gradually being eliminated. These difficulties raise a crucial question, which concerns all numerical solutions of complex problems; namely, how good are the resulting numerical solutions? Where exact-analytical solutions or pertinent experimental results are on hand, the previous question can be readily answered. In our present problem we have on hand the shockless supercritical hodograph solutions calculated by Nieuwland, and will shortly have two-dimensional, high Reynolds number tests by Rainbird for the NACA 64A-410 airfoil, which will serve for comparison purposes. Although the calculation for the Nieuwland profile requires further refinement, and a high Reynolds number comparison test is yet to be obtained for the NACA 64A-410 profile, we hope that the present results will serve to demonstrate the potential of the present unsteady finite difference procedure.
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