The development of the shuttle-like technology demonstrator PHOENIX is intended to proof the feasibility of a future European reusable space transportation system. The present work focuses on aerodynamic solutions for the clean-configuration of PHOENIX by three-dimensional Euler computations. Details on the structured grid generation process using the interactive MegaCads soft ware are discussed and a converged solution for supersonic inviscid flow is presented. The agreement of the obtained aerodynamic coefficients with wind tunnel and design data is favorable. Preliminary work has started on viscous hypersonic flow computations for different flight conditions.
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