Abstract: An highly efficient computer program for analysis of 3-D transonic conservative full-potential flowfields about axisymmetric and asymmetric fuselage configurations at nonzero incidence and nonzero sideslip has been developed according to Hoist's highly efficient algorithm of finite difference method. The nearly orthogonal bodyfitted C-O type and H-O type grids, obtained by algebraic method, are used in the computation. Calculations were performed for hemisphere-cylinder, ogive-cylinder and noncircular sectional fuselage with its canopy and the results obtained agree very well with available data of experiments and other theories. It is shown that the present method can be applied not only to subsonic free streams (Ma<1) but also to supersonic free streams (Ma), and so it covers the calculations of all the range of transonic free streams.

Key words: transonic flow, fuselage, finite difference method