A description will be presented of a computer program system that is being used for the prediction of aircraft steady aerodynamic characteristics. Properties of the system are described from two different viewpoints. One is that of the aerodynamic designer, who needs an information system to predict lift, moment and drag characteristics and to analyse configuration performance improvements. The other is that of the computational fluid dynamicist, whose responsibility it is to deliver a reliable information system. The system to be described consists of a geometry pre-processor, a panel method, a transonic flow code, a 3D laminar/turbulent boundary layer program and an aerodynamic data analysis post-processor. The usefulness of the results have been validated by comparison with results of wind tunnel tests for a number of transport- type wing-body configurations. Paper presented at the 3rd AIAA/ASME Joint Fluids, Plasma, Thermophysics and Heat Transfer Conference, June 7-11, 1982, St. Louis, Missouri, USA.