Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method

doi:10.1088/1674-1056/abf7ad

中国物理B ›› 2021, Vol. 30 ›› Issue (7): 74701-074701.doi: 10.1088/1674-1056/abf7ad

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method

Guangming Guo(郭广明)^†, Hao Chen(陈浩), Lin Zhu(朱林), and Yixiang Bian(边义祥)

College of Mechanical Engineering, Yangzhou University, Yangzhou 225127, China

收稿日期:2021-02-16 修回日期:2021-04-02 接受日期:2021-04-14 出版日期:2021-06-22 发布日期:2021-07-09
通讯作者: Guangming Guo E-mail:gmguo@yzu.edu.cn
基金资助:
Project partly supported by the National Natural Science Foundation of China (Grant No. 11802264) and the Natural Science Foundation of Jiangsu Province, China (Grant No. BK20180896).

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method

Guangming Guo(郭广明)^†, Hao Chen(陈浩), Lin Zhu(朱林), and Yixiang Bian(边义祥)

College of Mechanical Engineering, Yangzhou University, Yangzhou 225127, China

Received:2021-02-16 Revised:2021-04-02 Accepted:2021-04-14 Online:2021-06-22 Published:2021-07-09
Contact: Guangming Guo E-mail:gmguo@yzu.edu.cn
Supported by:
Project partly supported by the National Natural Science Foundation of China (Grant No. 11802264) and the Natural Science Foundation of Jiangsu Province, China (Grant No. BK20180896).

摘要/Abstract

摘要： Near space has been paid more and more attentionin recent years due to its military application value. However, flow characteristics of some fundamental configurations (e.g., the cavity) in near space have rarely been investigated due to rarefied gas effects, which make the numerical simulation methods based on continuous flow hypothesis lose validity. In this work, the direct simulation Monte Carlo (DSMC), one of the most successful particle simulation methods in treating rarefied gas dynamics, is employed to explore flow characteristics of a hypersonic cavity with sweepback angle in near space by considering a variety of cases, such as the cavity at a wide range of altitudes 20-60 km, the cavity at freestream Mach numbers of 6-20, and the cavity with a sweepback angle of 30°-90°. By analyzing the simulation results, flow characteristics are obtained and meanwhile some interesting phenomena are also found. The primary recirculation region, which occupies the most area of the cavity, causes pressure and temperature stratification due to rotational motion of fluid inside it, whereas the pressure and temperature in the secondary recirculation region, which is a small vortex and locates at the lower left corner of the cavity, change slightly due to low-speed movement of fluid inside it. With the increase of altitude, both the primary and secondary recirculation regions contract greatly and it causes them to separate. A notable finding is that rotation direction of the secondary recirculation region would be reversed at a higher altitude. The overall effect of increasing the Mach number is that the velocity, pressure, and temperature within the cavity increase uniformly. The maximum pressure nearby the trailing edge of the cavity decreases rapidly as the sweepback angle increases, whereas the influence of sweepback angle on velocity distribution and maximum temperature within the cavity is slight.

关键词: flow characteristics, cavity with sweepback angle, hypersonic flow, near space, DSMC

Abstract: Near space has been paid more and more attentionin recent years due to its military application value. However, flow characteristics of some fundamental configurations (e.g., the cavity) in near space have rarely been investigated due to rarefied gas effects, which make the numerical simulation methods based on continuous flow hypothesis lose validity. In this work, the direct simulation Monte Carlo (DSMC), one of the most successful particle simulation methods in treating rarefied gas dynamics, is employed to explore flow characteristics of a hypersonic cavity with sweepback angle in near space by considering a variety of cases, such as the cavity at a wide range of altitudes 20-60 km, the cavity at freestream Mach numbers of 6-20, and the cavity with a sweepback angle of 30°-90°. By analyzing the simulation results, flow characteristics are obtained and meanwhile some interesting phenomena are also found. The primary recirculation region, which occupies the most area of the cavity, causes pressure and temperature stratification due to rotational motion of fluid inside it, whereas the pressure and temperature in the secondary recirculation region, which is a small vortex and locates at the lower left corner of the cavity, change slightly due to low-speed movement of fluid inside it. With the increase of altitude, both the primary and secondary recirculation regions contract greatly and it causes them to separate. A notable finding is that rotation direction of the secondary recirculation region would be reversed at a higher altitude. The overall effect of increasing the Mach number is that the velocity, pressure, and temperature within the cavity increase uniformly. The maximum pressure nearby the trailing edge of the cavity decreases rapidly as the sweepback angle increases, whereas the influence of sweepback angle on velocity distribution and maximum temperature within the cavity is slight.

Key words: flow characteristics, cavity with sweepback angle, hypersonic flow, near space, DSMC

中图分类号: (Channel flow)

47.27.nd

47.40.Ki (Supersonic and hypersonic flows) 47.11.Mn (Molecular dynamics methods) 47.45.-n (Rarefied gas dynamics)

Guangming Guo(郭广明), Hao Chen(陈浩), Lin Zhu(朱林), and Yixiang Bian(边义祥). Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method[J]. 中国物理B, 2021, 30(7): 74701-074701.

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Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method

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