尾喷管内部及其射流流场的数值模拟

推进技术 ›› 2000, Vol. 21 ›› Issue (3): 53-55.

尾喷管内部及其射流流场的数值模拟

王松涛,冯国泰,王仲奇,袁宁,张振家

哈尔滨工业大学能源科学与工程学院!黑龙江哈尔滨150001;哈尔滨工业大学能源科学与工程学院!黑龙江哈尔滨150001;哈尔滨工业大学能源科学与工程学院!黑龙江哈尔滨150001;哈尔滨工业大学能源科学与工程学院!黑龙江哈尔滨150001;航天机电集团公司31所!北京100074

发布日期:2021-08-15
基金资助:
国家自然科学基金;教育部博士后基金

Numerical simulation of performeance and jet flowfield of the nozzle

School of Energy Science and Engineering , Harbin Inst.of Technology,Harbin 150001,China;School of Energy Science and Engineering , Harbin Inst.of Technology,Harbin 150001,China;School of Energy Science and Engineering , Harbin Inst.of Technology,Harbin 150001,China;School of Energy Science and Engineering , Harbin Inst.of Technology,Harbin 150001,China;The 31st Research Inst.,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

摘要： 通过求解三维 N- S方程 ,对某型发动机尾喷管在亚临界及超临界状态下的性能进行了数值模拟 ,尤其对喷管射流流场及其对喷管内部流动的影响进行了研究。差分格式采用具有 TVD性质的三阶精度的 Godunov格式 ,射流场及内部流场间采用分区算法。数值试验表明 ,所采用的算法可以很好地处理来自于任意方向上的任意间断

关键词: 尾喷管;射流;区域分裂算法;数值仿真

Abstract: The performance of nozzle on subcritical and supercritical condition was numerical simulated.The effect of nozzle jet flowfield performance on nozzle inner flowfield wsa also studied. A third order Godunov type algorithm which has TVD property was employed .In order to simulate jet flow field domain decomposition method and chimeral grid was also employed. Rieman problem was constructed on zonal boundary ,numerical test show that this method could treat arbitrary discontinuty from arbitrary direction well.

Key words: Tail nozzle;Jet flow;Domain decomposition;Numerical simulation

王松涛,冯国泰,王仲奇,袁宁,张振家. 尾喷管内部及其射流流场的数值模拟[J]. 推进技术, 2000, 21(3): 53-55.