The need for timely and accurate analysis of engine-airframe integration issues is addressed. It is shown that the present formulation allows the analysis of wing-body-nacelle configurations to be performed in a matter of hours on typical workstation class computers. In this work a previously developed three-dimensional unstructured Full Potential formulation is used to analyze the inviscid flow field about a generic low-wing transport configuration with nacelles. The results compare favorably with the available experimental data obtained in the NASA Langley 16-Foot wind tunnel. Specifically, the nacelle-pylon-wing region flow field is accurately predicted by the present method.