一种双斜切双压缩面进气道性能的数值模拟  

Numerical simulation of a dual-swept/dual-ramp inlet

作　　者：谭慧俊[1] 郭荣伟[1] 

机构地区：[1]南京航空航天大学动力工程系,江苏南京210016

出　　处：《空气动力学学报》2001年第3期338-343,共6页Acta Aerodynamica Sinica

摘　　要：采用LU SGS隐式推进方法及ROE的通量差分分裂格式 ,结合带非线性限量因子的MUSCL插值方法编写了雷诺平均的三维N S方程的数值求解程序 ,并借助该流场计算程序研究了一种双斜切双压缩面进气道在未经流场控制情况下的流动结构和气动性能(M =1.9,H =11Km)。计算结果表明 :所编制的流场计算程序能够准确快速地求解三维粘性流场 ,并对流场间断具有较高的分辨率 ;所研究的进气道即使在未经流场控制的情况下也具有较高的总压恢复系数 ,这体现了双斜切双压缩面进气道总压恢复系数高的优点 ,但由于流场中存在分离流动 ,应采取抽吸附面层等流场控制措施。Combined with the LU SGS implicit scheme and MUSCL interpolation method, Roe's approximate Riemann scheme is applied to develop a code for 3 Dimensional compressible Navier Stokes equations. With this code the flow field structure and aerodynamic performance of a dual swept/dual ramp inlet without flow field control is investigated at M =1.9, H =11Km. The calculated results show that: (a) the code developed in this paper is reliable to solve 3 Dimensional compressible flow field, it also possesses the quality of high resolution and sharp converge curve; (b) even without any effort of flow field control, the inlet under investigation does embody the advantage of high total pressure recovery of common dual swept/dual ramp inlet, but further effort has to be exerted to refrain the local separation for higher performance.

关 键 词：双斜切双压缩面进气道 分离流动 总压恢复系数 数值方法 战斗机 流动控制 流场计算程序 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程] V211.3