侧喷干扰流场计算及分析  

Computation and Analysis of Lateral Jet Interaction Flowfields

作　　者：徐敏[1] 陈士橹[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《西北工业大学学报》2003年第3期259-262,共4页Journal of Northwestern Polytechnical University

基　　金：航天基金 2 0 0 0 CH0 80 9;西北工业大学博士创新基金 (2 0 0 0 13)资助

摘　　要：采用 NND格式 ,通过求解 N- S方程 ,对绕双锥旋成体超高声速主流中横向喷流干扰流场进行了数值模拟 ,计算给出了喷流前后压力系数分布以及喷流气动干扰放大系数随迎角变化关系 ,并且根据计算喷流干扰流场结果 ,分析了喷流放大因子随迎角变化趋势的物理成因。该计算结果与文献 [1 ]趋势一致。In the absence of detailed information in the literature about the effect of jet interaction--between a lateral jet and its hypersonic flow--and about lateral jet interaction amplification factor for a variety of missile geometries, we in China have to develop numerical simulation method for getting such detailed information. Section 1 deals with numerical simulation and has five subsections: Navier Stokes equations (subsection 1.1); B L (Baldwin Lomax) turbulence model (subsection 1.2); LU SGS (Lower Upper Symmetric Gauss Seidel) implicit time discretization scheme (subsection 1.3); NND (non osillatory, containing no free parameters and dissipative) space discretization scheme (subsection 1.4); boundary conditions (subsection1.5). Section 2 gives Eq.(5) as the formula for computing jet interaction amplification factor K . Section 3 takes as numerical example a cone body with lateral jet, with Mach number M =8 and angle of attack α=-15°, 0°, or 15°. Fig.2 shows what we use as computation grid, which densifies at jet nozzle. Fig.3 shows the longitudinal pressure distribution downstream and upstream of the nozzle. Table 1 shows that, when α is -15°, 0°, or 15° or, K is respectively 1.166 8, 0.990 1 or 0.956 3 respectively. Our results agree with those of Ref.1.

关 键 词：数值计算 喷流干扰效应 喷射混合流 干扰放大因子 

分 类 号：TP601[自动化与计算机技术—控制理论与控制工程] V44[自动化与计算机技术—控制科学与工程]