锥导乘波体构型的气动特性不确定度分析

Uncertainty analysis of aerodynamic characteristics for cone-derived waverider configuration

为研究锥导乘波体偏离设计条件下气动特性变化情况,采用稀疏的非嵌入式混沌多项式方法,对乘波体气动特性进行了不确定性量化及全局非线性灵敏度分析。首先,采用CATIA二次开发技术对锥导乘波体进行参数化建模;其次,在来流速度、温度、密度和迎角满足特定扰动的条件下,通过拉丁超立方试验设计生成样本,并采用CFD进行计算;最后,根据试验设计样本建立响应面,通过混沌多项式分析得到了乘波体气动力系数的不确定度。灵敏度分析结果表明,迎角在锥导乘波体的气动特性变化中起主导作用。对马赫数和压强的流场不确定性分析结果表明,气动特性变化主因是乘波体前缘处的压力泄漏,影响了上表面压力分布,导致了气动性能的改变。

To study the variation of aerodynamic performances of a cone-derived waverider under the off-design condition,a sparse non-intrusive polynomial chaos method along with nonlinear global sensitivity analysis are used to achieve the uncertainty quantification of aerodynamic characteristics of the waverider.A parametric model of the cone-derived waverider is constructed by the secondary development of CATIA software.Under the condition when the flow velocity,temperature,density as well as the angle of attack can satisfy the specific disturbances,the sample data are generated by experimental design of Latin Hypercube sampling and calculated by the CFD method.The uncertainty of the aerodynamic coefficients of the waverider is obtained by non-intrusive polynomial chaos analysis based on the response surface established by the preceding sample data.The sensitivity analysis results show that the angle of attack plays a leading role in the variation of aerodynamic characteristics of the cone-derived waverider.The uncertainty analysis of the flow field of Mach number and pressure indicates that the main reason for the the variation of aerodynamic characteristics is pressure leakage at the leading edge of the waverider,which affects the distribution of the upper surface pressure and leads to deterioration of aerodynamic performances.