Abstract
A procedure is developed for calculating the inviscid flow past slender sharp-nosed fuselages at arbitrary transonic Mach numbers. Nonaxisymmetric shapes with small camber and incidence can be represented. A revision of Spreiter and Alksne's solution for accelerating, locally near-sonic flow and an empirical description of shock wave strength and location are patched to the local linearization equations for locally subsonic and supersonic flows. The local linearization method and the transonic method of Oswatitsch are applied to calculation of flow past converging afterbodies downstream of semi-infinite cylinders at low supersonic Mach numbers down to one. Calculated pressure distributions are in good agreement with data.
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