亚跨超音速喷管内流场的整体矢通量分裂算法

FLUX VECTOR SPLITTING ALGORITHMS FOR THE WHOLE OF SUBSONIC-TRANSONIC-SUPERSONIC NOZZLE FLOWS

关键词:  亚音速流  跨音速流  超音速喷管  喷管气流  流动分布  数值计算

Key words:  Subsonic flow  Transonic flow  Supersonic nozzle  Nozzle flow  Flow distribution  Numerical calculation

摘要:

从N－S方程出发，采用先进的矢通量分裂算法，对亚跨超音速喷管内流场进行了整体模拟计算。文中对几种不同计算格式的计算效率进行了比较，给出了超音速占优混合流动的直接分割求解方法。计算采用代数湍流模型，跨音速段的计算结果同其它实验和计算结果进行了比较。计算中发现对出口边界条件进行亚音速、超音速和有回流分别处理很有必要；边界层内的M数沿壁面法向变化非常快；不同壁温条件和不同的流动Re数均会改变边界层的厚度。

Abstract:

Presents flux-vector splitting methods based on Navier-Stokes equation to simulatewhole subsonic, transonic and supersonic flowfields in a nozzle. The computational efficiency of severaldifferent schemes are compared with each other and the direct solution by flowfield partitioning isused. The algebraic model is used for the turbulent calcuiations. The computed results of transonicflow are compared to the test and other’s computed results. It has been discovered that it is necessaryto deal with the subsonic, supersonic or reverse flow boundary conditions respectively at the outlet;The Mach number in the boundary layer changes very sharply along the direction perpendicular to thewall; The change of wall temperature or Re number can lead to the change of the thickness ofboundary layer.