Guided under the idea of parameter design, this paper optimized the cone and osculating cone derived waveriders, and an elemtary study of aerodynamic heat was carried.
在参数化设计思想的指导下,着重对锥导和吻切锥乘波构型进行了优化设计工作,对气动热的计算进行了初步的探讨,并得出了相应的结论。
参考来源 - 高速乘波飞行器气动布局设计研究·2,447,543篇论文数据，部分数据来源于NoteExpress
本论文进行了高超声速弹丸的气动热研究。
In this thesis, the aerodynamic heating methods of hypersonic projectile are presented.
对超高音速火箭的飞行载荷和气动热进行了分析计算。
The flight loads and dynamic heating of the rocket during flight in a high supersonic velocity are also analyzed and calculated.
在气动热计算中，应直接观察热流数据的收敛，确保得到真正的收敛解。
In order to get the convergence solution it is necessary to monitor the convergence of heat transfer data directly.
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