Numerical simulation of 3D supersonic asymmetric truncated nozzle based on k-kL algebraic stress model  

作　　者：Gang WANG Shuai ZHANG Jifa ZHANG Yao ZHENG 

机构地区：[1]School of Aeronautics and Astronautics,Zhejiang University,Hangzhou,310027,China

出　　处：《Journal of Zhejiang University-Science A(Applied Physics & Engineering)》2025年第3期238-251,共14页浙江大学学报(英文版)A辑(应用物理与工程)

基　　金：supported by the Zhejiang Provincial Key Research and Development Program of China(No.2020C01020).

摘　　要：The nozzle is a critical component responsible for generating most of the net thrust in a scramjet engine.The quality of its design directly affects the performance of the entire propulsion system.However,most turbulence models struggle to make accurate predictions for subsonic and supersonic flows in nozzles.In this study,we explored a novel model,the algebraic stress model k-kL-ARSM+J,to enhance the accuracy of turbulence numerical simulations.This new model was used to conduct numerical simulations of the design and off-design performance of a 3D supersonic asymmetric truncated nozzle designed in our laboratory,with the aim of providing a realistic pattern of changes.The research indicates that,compared to linear eddy viscosity turbulence models such as k-kL and shear stress transport(SST),the k-kL-ARSM+J algebraic stress model shows better accuracy in predicting the performance of supersonic nozzles.Its predictions were identical to the experimental values,enabling precise calculations of the nozzle.The performance trends of the nozzle are as follows:as the inlet Mach number increases,both thrust and pitching moment increase,but the rate of increase slows down.Lift peaks near the design Mach number and then rapidly decreases.With increasing inlet pressure,the nozzle thrust,lift,and pitching moment all show linear growth.As the flight altitude rises,the internal flow field within the nozzle remains relatively consistent due to the same supersonic nozzle inlet flow conditions.However,external to the nozzle,the change in external flow pressure results in the nozzle exit transitioning from over-expanded to under-expanded,leading to a shear layer behind the nozzle that initially converges towards the nozzle center and then diverges.

关 键 词：Supersonic nozzle Turbulence model Numerical simulation Performance analysis 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]