非线性EASM在激波与湍流边界层相互作用中的数值应用

Numerical application of nonlinear EASM model to the interaction between shock waves/turbulent boundary layer

采用基于k-ω湍流模型的非线性显式代数应力模型(EASM)对超燃冲压发动机常用的超声速凹槽、压缩拐角和侧壁压缩进气道简化模型的激波与湍流边界层的相互作用进行了计算,主要研究了EASM模型对壁面压强、摩阻、Stanton数和壁面摩擦力线的计算精度,计算结果与SST(shear stress transport)模型进行了比较.EASM模型对壁面压强、摩阻和Stanton数的计算精度较高,值得进一步推广应用.在壁面热流和摩擦力线的计算中EASM模型比SST模型的精度更高.

The nonlinear explicit algebraic stress model（EASM） in k-ω form was used to compute the interaction between shock wave and turbulent boundary layer of supersonic cavity,compression corner and simplified model of side-compression inlet which are usually used in scramjet engine.The main focus was computational resolution of EASM model on wall pressure,friction,Stanton number and skin friction lines.The computational results of EASM model were compared with those of SST（shear stress transport） model.EASM model has better computational resolution on wall pressure,friction and Stanton number so that it can be generalized.EASM model is better than SST model in computation of Stanton number and skin friction lines.