Optimal computational methodology for HSCT design: interdisciplinary coupling

摘要

A number of aircraft analysis and design problems can be performed in a "quasi-static" fashion where performance is evaluated at different positions in the flight trajectory. A key element is determining the "state" of the air-craft- flow field response which involves an iterative coupling between the two appropriate analysis codes. The problem which is of concern here is that of optimally integrating a propulsion system within some airframe construct, a classic multidisciplnary design.