Transonic Full Potential equation has been computed for the flowfield past bodies of revolution with angle of attack. The present method employs the basic features of JAMESON's rotated difference scheme, CALSON's relaxation method, the introduction of the perturbation potential in cylindrical cartesian coordinates, and the appropriate treatment of singular line occured in 3-D cylindrical one. The physical properties of transonic flow about staged launch vehicles having nosebody of cone, ellipsoid, and give type are investigated. Therefore, the mutual interference between forebody and flare is also analyzed quantitatively. The calculated flow characteristics are presented through the plot of pressure coefficient curve, isomach line, velocity vector, and isobaric contour at some constant foreview planes, or meridional sideview one. Comparison of the calculated results with the experimental data reported earlier shows good agreement.