壁面压升可控的高超轴对称进气道优化设计  

Optimization design of hypersonic axisymmetric inlet withcontrollable law of wall pressure rise

作　　者：向有志[1] 张堃元[1] 王磊[1] 高雄[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2011年第10期2193-2199,共7页Journal of Aerospace Power

基　　金：国家自然基金重大专项(90916029)

摘　　要：采用有旋特征线理论,研究了沿程压升规律可控的轴对称物理壁面设计方法,基于该方法,结合替代模型多目标优化设计压缩面,基于优化结果,设计了一种高超声速轴对称进气道,对其进行了数值研究,并与常规双锥、三锥轴对称进气道进行了比较.结果表明:该进气道长度比双锥进气道缩短捕获半径的32.5%;设计点其性能介于双锥与三锥之间;起动点其流量系数比双锥和三锥分别提高8.24%和12.60%,总压恢复系数比双锥和三锥分别提高4.06%和2.50%.The design method of axisymmetric wall boundary with a controllable law of wall pressure rise was investigated using the theory of rotational characteristics.With this design method,multi-objective optimization of the compression surface was carried out on the basis of surrogate models,and then a hypersonic axisymmetric inlet was designed using the optimal solutions.The inlet was investigated through numerical simulation,and was compared with the normal double-cone and triple-cone inlet.The results show that the length of new inlet is reduced by 32.5% of the radius than the double-cone inlet;under the design point,the performance of the new inlet lies between the double-cone and triple-cone inlet;under the start point,the flow capture ratio is improved by 8.24% and 12.60%,and the total pressure recovery is improved by 4.06% and 2.50% than the double-cone and triple-cone inlet,respectively.

关 键 词：高超声速轴对称进气道 壁面压升规律 弯曲激波 曲面压缩型面 优化设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]