Abstract: The flow region around the wing-body combination is transformed by locad Jonkowski transformation into the one around a wing alone for the case with the body of circular cross section. The body-fitted "O" mesh around the transformed wing alone is constructed for each grid section by numerical conformal mapping, and is then, transformed back to form 3 -D bodyfitted mesh around the given wing-body combination. The transonic flow computation is performed by the use of conservative full-potential equation with exact boundary conditions and the efficient iteration scheme in finite difference method AF2. It is shown that only a few changes needed to expand the computer program for wing alone to cover wing-body combinations. The presented method is limited to the combinations which consist of the bodies of finite or infinite lengths with curved axes and circular cross sections, and the wing of arbitrary planform with finite wing tip. The computations for the combination with highly tapered and swept wing, nevertheless, is still a difficult problem.