文档介绍：Chinese Journal of Aeronautics 24 （2011） xx-xx
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Chinese Journal of ed, un der high-altitude, high-speed and afterburning conditions. Two completely different air-inlet schemes of ejecting channel almost achieve the same effect in cooling inner flaps （英文摘要应不少于150词；包含研究的目的、方法、结果和结论；通常用一 般现在时，除非有明显的过去时间指示词出现）
Keywords: transonic flow; unsteady flow; full-potential equation （5-8 个，建议其中 1-2 个选自 EI controlled term 词表）
Introduction 1
The computation method of unsteady transonic flow based on N-S equations should be best accurate, but to three-dimensional complex problems, it can be achieved only on large computers, and moreover, the results are not ideal sometimes"]. A viscous/inviscid interaction method is an applicable one and the com putation time can be reduced by two orders.
The method to solve the full-potential equation over transonic unsteady forces on wings has been devel- oped[2-3], but to assemblies, it is not mature, and the research works are continuously carried ong.
The key to compute the unsteady aerodynamic forc es is to generate dynamic grids efficiently. In the pre sent paper, an algebraic method and rapid deforming technique are used to generate three-dimensional boundary-fitted dynamic grids for assemblies. The conservative full-potential equation is solved by a time-accurate approximate factorizati