高速有迎角圆锥绕流底部复杂流动结构研究

陈智; 马乐; 靳旭红; 艾邦成

doi:10.7638/kqdlxxb-2024.0019

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高速有迎角圆锥绕流底部复杂流动结构研究

研究论文 | 更新时间：2026-05-28

- 高速有迎角圆锥绕流底部复杂流动结构研究
- Research on complex flow structures at the base of high-speed conical flow with an angle of attack
- 空气动力学学报 2025年43卷第5期页码：11-30
- 作者机构：
  
  1. 中国航天空气动力技术研究院,北京,100074
  2. 航天飞行器气动热防护实验室,北京,100074
- 作者简介：
  
  陈智*（1983—），男，湖北武汉人，研究员，研究方向：气动加热预测方法. E-mail：chenzhi@live.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0019
  中图分类号： V19;V411.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
陈智, 马乐, 靳旭红, 等. 高速有迎角圆锥绕流底部复杂流动结构研究[J]. 空气动力学学报, 2025, 43(5): 11−30.

CHEN Zhi, MA Le, JIN Xuhong, et al. Research on complex flow structures at the base of high-speed conical flow with an angle of attack[J]. 2025, 43(5): 11-30.
陈智, 马乐, 靳旭红, 等. 高速有迎角圆锥绕流底部复杂流动结构研究[J]. 空气动力学学报, 2025, 43(5): 11−30. DOI： 10.7638/kqdlxxb-2024.0019

CHEN Zhi, MA Le, JIN Xuhong, et al. Research on complex flow structures at the base of high-speed conical flow with an angle of attack[J]. 2025, 43(5): 11-30. DOI： 10.7638/kqdlxxb-2024.0019.

摘要

在非零攻角下，圆锥外形底部流动将失去轴对称性，其流动结构将显著区别于零攻角工况。本文以Reentry-F飞行器飞行试验中高度为37.5 km、马赫数为19.13的工况为基准工况，利用数值模拟方法开展了5°半锥角圆锥外形非轴对称层流底部流动结构研究，分析了来流攻角、马赫数、雷诺数等因素对底部流动结构以及底面热流、压力等参数的影响规律。研究结果表明：与零攻角时的锥形回流区不同，非零攻角下回流区为非规则形状，且回流区长度较零攻角大幅减小，最大减小了44.6%。随着攻角增大，底部涡与前体背风侧涡发生相互作用，导致回流区长度随攻角增大呈现先减小后增大再减小的非线性变化规律；模型底面的无量纲压力、斯坦顿数峰值总体上呈现先减小后增大的趋势。随着马赫数增大，流动的可压缩性增强，小尺度的涡面及波系结构减少，回流区长度单调减小，无量纲压力和斯坦顿数峰值则分别呈单调增大、单调减小的变化趋势。雷诺数对波系结构的影响相对较小，随单位雷诺数增大，黏性效应减弱，回流区背风侧凹陷逐渐增强，回流区长度单调增加，无量纲压力及斯坦顿数峰值均单调减小。

Abstract

Under non-zero angle of attack

the near-wake flow of a conical shape vehicle loses its axisymmetric nature

and the flow structure significantly differs from that under the condition of zero angle of attack. In the present study

we selected a reference state from the Reentry-F flight experiment of an altitude of 37.5 km and Mach number of 19.13

and conducted a numerical study on the laminar near-wake flow structure of a 5° half-cone angle circular cone. Influences of the angle of attack

Mach number

Reynolds number

etc.

on the near-wake flow structures

pressure and heat flux on the base surface were analysed. The results indicated that

in contrast to the conical shape at zero angle of attack

the recirculation region at non-zero angles of attack displayed an irregular shape

and its length decreased significantly

up to 44.6%. As the angle of attack increased

the near-wake vortices and the leeward vortices of the forebody could interact with each other

which results in a trend of decreasing-increasing-decreasing of the recirculation zone length. The non-dimensional pressure and peak values of the Stanton number showed a decreasing-increasing trend with the increase of the angle of attack. As the Mach number increases

the flow compressibility got stronger

leading to a monotonic decrease in the length of small-scale vortex surfaces and wave structures in the recirculation zone

while the dimensionless peak pressure increased monotonically

and the peak Stanton number decreased monotonically. The influence of Reynolds number on the wave structures was relatively small. As the unit Reynolds number increased

the viscous effect weakened

resulting in an increase in the leeward depression of the recirculation zone and a monotonic increase in the length of the recirculation zone

with both the dimensionless peak pressure and Stanton number decreasing monotonically.

关键词

Keywords

references

SCHUYLER H W, JOHANSEN C T. Mechanisms in the hypersonic laminar near wake of a blunt body[J]. Journal of Fluid Mechanics, 2018, 839: 33−75. doi: 10.1017/jfm.2017.902

BAIDYA R, SCHARNOWSKI S, DE SILVA C M, et al. Investigation of a near-field cylinder wake in the subsonic, transonic, and supersonic regimes[J]. AIAA Journal, 2023, 61(12): 5415−5428. doi: 10.2514/1.J063163

KHAN A, RAJENDRAN P, SIDHU J S S. Passive control of base pressure: A review[J]. Applied Sciences, 2021, 11(3): 1334. doi: 10.3390/app11031334

LAMB J P, OBERKAMPF W L. Review and development of base pressure and base heating correlations in supersonic flow[J]. Journal of Spacecraft and Rockets, 1995, 32(1): 8−23. doi: 10.2514/3.26569

THASU P S, DUVVURI S. Strouhal number universality in high-speed cylinder wake flows[J]. Physical Review Fluids, 2022(7): L081401. doi: 10.1103/PhysRevFluids.7.L081401

CARPENTER P W, TABAKOFF W. Survey and evaluation of supersonic base flow theories: N68-36011[R]. NASA, 1968.

DECHANT L J, ROBBINS B A, STACK C, et al. Base pressure fluctuation modeling: Theory, simulation and measurement[C]//AIAA SCITECH 2023 Forum, United States, 2023. doi: 10.2514/6.2023-1040

MOFFEIT N, KUMAR R, GUSTAVSSON J. Experimental characterization of the base flow of a slender cone at supersonic speeds[C]//AIAA SCITECH 2023 Forum, United States , 2023. doi: 10.2514/6.2023-1191

STACK C, ROBBINS B, ZHANG Y, et al. Influence of blunt-body base protuberances on near-wake unsteadiness: ICCFD11-4204[R]. NASA, 2022.

HERRIN J L, DUTTON J C. Supersonic base flow experiments in the near wake of a cylindrical afterbody[J]. AIAA Journal, 1994, 32(1): 77−83. doi: 10.2514/3.11953

BOURDON C, SMITH K, DUTTON J C, et al. Planar visualizations of large-scale turbulent structures in axisymmetric supersonic base flows[C]//36th AIAA Aerospace Sciences Meeting and Exhibit, United States, 1998. doi: 10.2514/6.1998-624

KIRCHNER B M, ELLIOTT G S, DUTTON J C. Hairpin vortex structures in a supersonic, separated, longitudinal cylinder wake[J]. Physics of Fluids, 2020, 32(4): 046103. doi: 10.1063/1.5143880

DEBLAUW B, ELLIOTT G, DUTTON C. Active control of supersonic base flows with electric arc plasma actuators[J]. AIAA Journal, 2014, 52(7): 1502−1517. doi: 10.2514/1.J052585

ROBERT L W, ERNEST V Z. Flight measurements of boundary-layer transition on a 5 degree half-angle cone at a free-stream Mach number of 20 (Reentry-F): NASA-TM-X-2253[R]. NASA, 1971.

JAMES L D, HOWARD S C. Analysis of base pressure and base heating on a 5 degree half-angle cone in free flight near Mach 20 (Reentry-F): NASA-TM-X-2468[R]. NASA, 1972.

BARNHARDT M, CANDLER G. Detached eddy simulation of hypersonic base flows during atmospheric entry[C]// 9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, San Francisco, California. Reston, Virginia: AIAA, 2006. doi: 10.2514/6.2006-3575

BARNHARDT M, CANDLER G V. Detached-eddy simulation of the Reentry-F flight experiment[J]. Journal of Spacecraft and Rockets, 2012, 49(4): 691−699. doi: 10.2514/1.A32128

KAWAI S, FUJII K. Computational study of a supersonic base flow using hybrid turbulence methodology[J]. AIAA Journal, 2005, 43(6): 1265−1275. doi: 10.2514/1.13690

SIMON F, DECK S, GUILLEN P, et al. Reynolds-averaged Navier-Stokes/large-eddy simulations of supersonic base flow[J]. AIAA Journal, 2006, 44(11): 2578−2590. doi: 10.2514/1.21366

DAS P, DE A. Numerical investigation of flow structures around a cylindrical afterbody under supersonic condition[J]. Aerospace Science and Technology, 2015, 47: 195−209. doi: 10.1016/j.ast.2015.09.032

ZHUO C F, FENG F, WU X S. Research on base flow field and aerodynamic characteristics of the supersonic base bleed projectile[J]. ACTA AERODYNAMICA SINICA, 2014, 32(6): 783−790(in Chinese). doi: 10.7638/kqdlxxb-2013.0021

WEIDNER S, HRUSCHKA R, LEOPOLD F. Influence of swirl on the supersonic wake flow structure behind blunt-based axisymmetric afterbodies[J]. Journal of Fluid Mechanics, 2021, 925: A21. doi: 10.1017/jfm.2021.465

TRAN T H, DAO C T, LE D A, et al. Aerodynamic drag of axisymmetric models with different boattail angles under subsonic and supersonic flow conditions[J]. Journal of Mechanical Science and Technology, 2023, 37(12): 6523−6535. doi: 10.1007/s12206-023-1124-z

DAVIES R, HIGHSMITH F, GASTION C, et al. Infrasonic characterization of the falcon hypersonic technology vehicle (HTV-2) test[R]. Advanced Technologies Enabling Long-Duration Hypersonic Flight for Prompt Global Reach, 2011.

SATCHELL M J, LAYNG J M, GREENDYKE R B. Numerical simulation of heat transfer and chemistry in the wake behind a hypersonic slender body at angle of attack[J]. Aerospace (Basel), 2018, 5(1): 30. doi: 10.3390/aerospace5010030

MARCILLAT J. An experimental study of the near wake of a slender cone at varying incidence at Ma ∞ = 7[J ] . Journal of Fluid Mechanics, 1974, 63(1): 195−208. doi: 10.1017/S0022112074001091

BOSWELL B A, DUTTON J C. Flow visualizations and measurements of a three-dimensional supersonic separated flow[J]. AIAA Journal, 1999, 39: 113−121. doi: 10.2514/2.1277

BOSWELL B A, DUTTON J C. Velocity measurements in a three-dimensional compressible base flow[J]. AIAA Journal, 2003, 41(5): 785−794. doi: 10.2514/2.2040

GAITONDE D V. Mean flowfield structure of a supersonic three-dimensional base flow[J]. Journal of Aircraft, 2010, 47(2): 368−382. doi: 10.2514/1.45144

CHEN Z, PAN H L, ZHANG L. Numerical study on the supersonic near-wake flow structures of a cylinder at an angle of attack[J]. Computers Fluids, 2021, 228: 105043. doi: 10.1016/J.COMPFLUID.2021.105043

LIN T, SPROUL L, KIM M, et al. Hypersonic reentry vehicle wake flow fields at angle of attack[C]// 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2006. doi: 10.2514/6.2006-582

PLACCO L, COGO M, BERNARDINI M, et al. Large-Eddy simulation of the unsteady supersonic flow around a Mars entry capsule at different angles of attack[J]. Aerospace Science and Technology, 2023, 143: 108709. doi: 10.1016/j.ast.2023.108709

PAN H L, LI J H, SHEN Q. A new numerical scheme and its application in multi-scale flow[J]. Journal of Propulsion Technology, 2015, 36(12): 1774−1780(in Chinese). doi: 10.13675/j.cnki.tjjs.2015.12.003

JEONG J, HUSSAIN F. On the identification of a vortex[J]. Journal of Fluid Mechanics, 1995, 285: 69−94. doi: 10.1017/S0022112095000462

HAMA F R. Experimental studies on the lip shock[J]. AIAA Journal, 1968, 6(2): 212−219. doi: 10.2514/3.4480

PAREDES P, VENKATACHARI B S, CHOUDHARI M M, et al. Toward transition modeling in a hypersonic boundary layer at flight conditions[C]// AIAA Scitech 2020 Forum, Orlando, FL. Reston, Virginia: AIAA, 2020. doi: 10.2514/6.2020-0103

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