攻角振荡对高超声速进气道性能影响数值模拟

推进技术 ›› 2011, Vol. 32 ›› Issue (4): 461-465.

攻角振荡对高超声速进气道性能影响数值模拟

李亭鹤,高瑞泽,李琪娜

中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074;中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074;中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074

发布日期:2021-08-15
作者简介:李亭鹤(1975—),男,博士,高级工程师,研究领域为计算流体力学。E-mail:litinghe@sina.com

Numerical simulation on effects of oscillatory angle of attackon performance of hypersonic inlet

Science and Technology on Scramjet Lab., The 31st Research Inst. of CASIC, Beijing 100074, China;Science and Technology on Scramjet Lab., The 31st Research Inst. of CASIC, Beijing 100074, China;Science and Technology on Scramjet Lab., The 31st Research Inst. of CASIC, Beijing 100074, China

Published:2021-08-15

摘要/Abstract

摘要： 应用重叠网格计算方法对高超声速飞行器出现攻角振荡时的发动机进气道的流场特性进行了数值模拟,给出了频率为10,20,40 Hz以及3°和5°振幅对进气道气动力、总压恢复系数和流量系数的影响,比较了飞行器在Ma∞=4,H=17 km爬升阶段和Ma∞=6,H=28 km巡航阶段攻角振荡对进气道性能参数的影响。计算结果表明,攻角的动态变化会造成进气道气动力、总压恢复系数和流量系数出现较大波动。

关键词: 高超声速进气道;攻角振荡;性能参数; 数值仿真

Abstract: Since the oscillation of angle of attack will bring adverse effects on the performance of hypersonic inlet, computational fluid dynamics method and overlapping grid method are used to investigate the oscillations of the aerodynamic forces, pressure recovery coefficient and mass flow coefficient of a typical 2D inlet. The effects of frequency at 0,0, 40 Hz and amplitude at 3°and 5°on inlet performance parameters are given in this paper, differences between climb phase with Ma∞=4 and H=17 km and cruise phase with Ma∞=6 and H=28 km of hypersonic aircraft are also presented. The results show that large oscillation occurs on aerodynamic force, pressure recovery coefficient and mass flow coefficient under the unsteady movement. These adverse effects will bring much challenge to the hypersonic craft and engine design if the oscillation of angle of attack could not be avoid. 

Key words: Hypersonic inlet; Oscillation of attack angle; Performance parameter; Numerical simulation

李亭鹤,高瑞泽,李琪娜. 攻角振荡对高超声速进气道性能影响数值模拟[J]. 推进技术, 2011, 32(4): 461-465.