矢通量分裂隐式有限体积法解超音速喷流强干扰流场

 发展了用于轴对称流场，任意非正交曲线网格下的矢通量分裂隐式有限体积法；统一了二维和轴对称流场计算的表达式。该方法对粘性通量项进行了分解和归类，考虑了包括交叉导数项在内的所有项对隐式增量的贡献。对带中心喷流的流动计算表明该方法收敛速度和计算精度均优于ＭａｃＣｏｒｍａｃｋ显式格式。横向喷流强干扰流场的计算初步揭示了姿控发动机喷流产生间接推力的机理，由此，设计中可降低对主发动机额定推力的要求

FLUX-SPLITTING IMPLICIT FINITE VOLUME METHOD FOR THE CALCULATION OF THE SUPERSONIC FLOW WITH STRONG INTERACTION OF A JET

A flux-splitting implicit finite volume method under an arbitary non-orthogonally curvilinear grid system is developed for the calculation of the axisymmetrical flow. The expression for the calculation of the two-dimensional and axisymmetric flow is unified. Decomposition and classification of the viscous flux are performed,so the contribution of all terms to the implicit increment,including the cross-derivative terms,is taken into account in this method The calculation of the flow with a centered jet shows that the method is superior to the MacCormack explicit scheme in both accuracy and convergence rate The computation of the strong interaction flow with transverse injection reveals primarily the producing mechanism of the indirectly propulsive force of the attitude control nozzle According to this,the requirement for the rated propulsive force of the nozzle can be degraded in desgin