Abstract
An aerodynamic design method and corresponding codes are developed for three dimensional multi-lifting surfaces at transonic flow. It is based on the “iterative residual correction” concept that is successfully used for transonic wing design and subsonic multi-lifting surface design. The up wind scheme is introduced into governing equations of multi-lifting surface design method and automatically acted when supersonic flow appears on the surface. A series of interface codes are programmed, including a target- pressure modification tool. Using the improved inverse aerodynamic design code, T A U code and interface codes, the transonic multi-lifting aerodynamic design software system is founded. Two cases of canardwing configuration have been performed to validate the method and codes. The results show that the convergence of analysis/design iteration is very good at higher speed transonic flow.
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