Numerical investigation on flow and aerothermal characteristics of rarefied hypersonic flows over slender cavities

被引:3
|
作者
Guo, Guangming [1 ]
Luo, Qin [2 ]
Wu, Jinwu [1 ]
机构
[1] Nanchang Hangkong Univ, Sch Aircraft Engn, Nanchang 330063, Peoples R China
[2] Nanchang Hangkong Univ, Coll Informat Engn, Nanchang 330063, Peoples R China
基金
中国国家自然科学基金;
关键词
Slender cavity; Aerothermal characteristics; Flow structures; Three-dimensional effect; Rarefied hypersonic flows; CONTINUUM; DSMC;
D O I
10.1016/j.ast.2023.108768
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Flow and aerothermal characteristics of rarefied hypersonic flows passing through slender cavities are investigated comprehensively using the direct simulation Monte Carlo (DSMC) method by various cases, such as the cavity with different depth-to-width ratios and different inclination angles, and the freestream at different altitudes and Mach numbers. The cavity depth-to-width ratio has a great influence on flow structures and gas density inside the cavity, but a slight effect on gas temperature inside the cavity and on heat flux over cavity surfaces. In comparison to the vertical cavity, the upstream-inclined cavity reduces the gas density and the hightemperature area inside the cavity, showing a decrease rate of gas density of about 53 % for phi = -45 degrees, while the downstream-inclined cavity greatly raises the gas density and slightly expands the high-temperature area, reaching a growth rate of gas density of about 114 % for phi = 45 degrees. As the freestream altitude increases from 50 to 80 km, the main vortex expands remarkably while the heat flux near the top of the aft wall decreases sharply, and a noteworthy finding is that the dimensionless temperature contours inside the cavity for the cases of H = 50, 60, and even 70 km seem to be unchanged. Compared with the case of Ma = 6, the maximum density inside the cavity is increased by about 5.5 times for the case of Ma = 30, and it is about 7.3 times for the maximum temperature inside the cavity. However, raising the freestream Mach number seems to not alter the streamline patterns inside the cavity. The three-dimensional effect reduces the maximum density inside the cavity by about 14.5 % to 17.4 % and results in a smaller main vortex compared with the two-dimensional (2D) cavity, and moreover, the slender cavity can weaken the three-dimensional effect due to its larger depth-to-width ratio and the relatively short cavity width. Besides, the vortex-transport theory is proposed, which can well explain the change of gas density inside the cavity for all cases considered in this work.
引用
收藏
页数:21
相关论文
共 50 条
  • [21] Investigation on the Opposing Jet in the Hypersonic Rarefied Flow over a Vehicle Based on the DSMC Method
    Shen, Yi
    Zhang, Jun
    Xu, Xiao
    Liu, Jing
    Zhang, Zhaoming
    Jiao, Yanmei
    ACTUATORS, 2022, 11 (06)
  • [22] Numerical investigation of hypersonic MHD flows
    Chen, G.
    Zhang, J. B.
    Lee, C. H.
    NEW TRENDS IN FLUID MECHANICS RESEARCH: PROCEEDINGS OF THE FIFTH INTERNATIONAL CONFERENCE ON FLUID MECHANICS, 2007, : 706 - 709
  • [23] Numerical investigation of hypersonic intake flows
    Krause, Martin
    Ballmann, Josef
    HIGH PERFORMANCE COMPUTING IN SCIENCE AND ENGINEERING '07, 2008, : 471 - 486
  • [24] Numerical simulation for the hypersonic flow structure and thermal environment of non-rectangular cavities in the rarefied slip regime
    Jin, Xuhong
    Yao, Yuzhu
    Cheng, Xiaoli
    Zhou, Jingyun
    Hangkong Dongli Xuebao/Journal of Aerospace Power, 2024, 39 (10):
  • [25] Numerical study of hypersonic rarefied-gas flows about a torus
    Riabov, VV
    JOURNAL OF SPACECRAFT AND ROCKETS, 1999, 36 (02) : 293 - 296
  • [26] VISCOUS AERODYNAMIC CHARACTERISTICS IN HYPERSONIC RAREFIED GAS FLOW
    PROBSTEIN, RF
    KEMP, NH
    JOURNAL OF THE AEROSPACE SCIENCES, 1960, 27 (03): : 174 - 192
  • [27] Investigation of periodic characteristics of perturbed flow over a slender body
    Zhao, Li
    Wang, Yankui
    Qi, Zhongyang
    HELIYON, 2023, 9 (05)
  • [28] Physical and Numerical Aspects of Simulating Rarefied Hypersonic Wedge Flow
    Santos, Wilson F. N.
    JOURNAL OF SPACECRAFT AND ROCKETS, 2010, 47 (03) : 394 - 404
  • [30] Effect of Nose Bluntness on Flowfield Over Slender Bodies in Hypersonic Flows
    Singh, D. J.
    Kumar, A.
    Tiwari, S. N.
    JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 1991, 5 (02) : 166 - 171