Modern high performance aircraft engines typically have variable geometry nozzles in order to operate at optimal throat areas and throat-to-exit area ratios over a wide range of flight conditions. Designing such a nozzle requires interaction between analysis disciplines such as mechanisms analysis, structural analysis, aerodynamics and thermodynamics. Two issues of importance are reliable data flow between the disciplines and design cycle time. An Exhaust Nozzle Analysis System (ENAS) was developed for evaluating designs of convergent-divergent two-dimensional nozzles. The system incorporates aerodynamic and thermodynamic analyses to allow concurrent engineering, in one automated system mechanism. The system provides the necessary interfaces between analysis codes and between analysis tools and empirical data. While the system described in this paper addresses the design of a single nozzle, the approach is generic and can be applied to any system where a number of disciplines such as mechanism analysis, aerodynamics, structural analysis, and thermodynamics are considered concurrently.