THE NEWTONIAN THEORY of impact has been shown to be useful for pressure calculations on the forward facing part of bodies moving at high speed. I t is now a familiar practice to use this information to calculate nonviscous velocities at the wall and then to estimate rates of heat transfer. This procedure is perhaps open to question; heat-transfer rates depend on velocity gradients which are not given by the Newtonian analysis. Nor can one obtain information on boundary-layer stability or all the body stability derivatives. I t seems, fore, inevitable that , as design proceeds with these hypersonic missiles, there will be a greater need for more accurate aerodynamic theories either to predict what will happen in unfamiliar flight conditions or to effect an extrapolation from a known test result to the design condition. A start in this direction has been made by the writer h 2 for two kinds of blunt bodies, one with a flat-disc face and the other with a hemispherical face. Our theory depends on the limiting THEORY
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Hyman Serbin (1958) studied this question.