Aerodynamic characteristics of high-pressure capturing wing configuration in multi-regime

TIAN Peng; LI Guangli; CUI Kai; LI Zhihui; ZHANG Jun

doi:10.7638/kqdlxxb-2020.0144

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Aerodynamic characteristics of high-pressure capturing wing configuration in multi-regime

更新时间：2026-05-28

- Aerodynamic characteristics of high-pressure capturing wing configuration in multi-regime
- Vol. 39, Issue 3, Pages: 11-20(2021)
- 作者机构：
  
  1. 北京航空航天大学航空科学与工程学院,北京,100191
  2. 中国科学院力学研究所高温气动国家重点实验室,北京,100190
  3. 中国科学院大学工程科学学院,北京,100049
  4. 中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2020.0144
  CLC： V221.3;V224
- Published：2021
- 稿件说明：
移动端阅览
田鹏, 李广利, 崔凯, 等. 高压捕获翼构型的跨流域气动特性[J]. 空气动力学学报, 2021, 39(3): 11−20.

TIAN Peng, LI Guangli, CUI Kai, et al. Aerodynamic characteristics of high-pressure capturing wing configuration in multi-regime[J]. 2021, 39(3): 11-20.
田鹏, 李广利, 崔凯, 等. 高压捕获翼构型的跨流域气动特性[J]. 空气动力学学报, 2021, 39(3): 11−20. DOI： 10.7638/kqdlxxb-2020.0144

TIAN Peng, LI Guangli, CUI Kai, et al. Aerodynamic characteristics of high-pressure capturing wing configuration in multi-regime[J]. 2021, 39(3): 11-20. DOI： 10.7638/kqdlxxb-2020.0144.

摘要

高压捕获翼（HCW）构型是一种满足高速飞行器高容积、高升力、高升阻比的设计需求的新型气动布局。最近研究表明，HCW构型能够提高飞行器在连续流区的升力和升阻比，缓解飞行器设计中高容积率与高升阻比间的矛盾。为探究该气动布局在过渡流域（70～100 km）的气动特性，以一种楔—平板组合的高压捕获翼原理性构型作为模型，采用直接模拟Monte Carlo （DSMC）方法，详细分析了该模型在典型高超声速条件（马赫数20）下的流场结构和壁面气动力/热分布。结果表明，随着飞行高度增加，稀薄效应增强，机体压缩产生的激波厚度增加，激波边缘逐渐模糊，机体与捕获翼之间的开放通道内出现压力干扰。同时，高压捕获翼表面的摩擦系数迅速上升，气动摩擦成为制约捕获翼构型升阻比的重要因素。针对这一问题，分析了捕获翼材料表面的适应系数对飞行器的气动力/热的影响，结果表明，降低适应系数可以显著减小壁面摩擦和热流量，可通过选用适应系数较小的表面材料进一步提高该类飞行器气动性能。

Abstract

High-pressure capturing wing (HCW) configuration is a novel aerodynamic design for hypersonic vehicles with large volume

high lift

and high lift-to-drag ratio. Recently

comprehensive studies have shown that HCW can effectively improve the lift force and the lift-to-drag ratio of vehicles in the continuous flow regime

and alleviate the contradiction between high volume and high lift-to-drag ratio in aircraft design. In order to explore the aerodynamic characteristics of HCW in different flow regimes (70~100 km)

a geometry of wedge-plate combination is taken as a simplified compu

tational model

and the direct simulation Monte Carlo (DSMC) method is employed to investigate the flow field and wall aerodynamic force/heat characteristics under typical hypersonic conditions (

= 20). The simulation results show that as the flight altitude increases

the aircraft-induced shock thickness increases

the shock edge gradually becomes fuzzy

and the pressure interference tends to occur in the open channel between the body and HCW. The friction coefficient of HCW increases rapidly with the increase of rarefaction

which becomes an important factor restricting the lift-to-drag ratio of HCW. Furthermore

the effect of accommodation coefficient on the aerodynamic force/heat of the aircraft increases with the rarefaction degree. Reducing the accommodation coefficient can significantly reduce the shear stress and heat flux of HCW

which is an efficient way to reduce the drag and aerodynamic heating

thus can improve the aerodynamic performance.

关键词

Keywords

references

蔡国飙, 徐大军. 高超声速飞行器技术[M]. 北京: 科学出版社, 2012.ISBN: 978-7-03-033062-8.

ZHU Y H, PENG W, XU R N, et al. Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles[J]. Chinese Journal of Aeronautics, 2018, 31(10): 1929-1953. doi: 10.1016/j.cja.2018.06.011.

VOLAND R T, HUEBNER L D, MCCLINTON C R. X-43A hypersonic vehicle technology development[J]. Acta Astronautica, 2006, 59(1-5): 181-191. doi: 10.1016/j.actaastro.2006.02.021.

WALKER S, SHERK J, SHELL D, et al. The DARPA/AF falcon program: the hypersonic technology vehicle #2 (HTV-2) flight demonstration phase[C ] //15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio. Reston, Virginia: AIAA, 2008.doi: 10.2514/6.2008-2539 .

KÜCHEMANN D. The aerodynamic design of aircraft[M]. FRS: Pergamon Press, 1978.

ANDERSON J D. Hypersonic and high-temperature gas dynamics[M]. American Institute of Aeronautics and Astronautics, 2006.

DING F, LIU J, SHEN C B, et al. An overview of research on waverider design methodology[J]. Acta Astronautica, 2017, 140: 190-205. doi: 10.1016/j.actaastro.2017.08.027.

HOLLAND S D, WOODS W C, ENGELUND W C. Hyper-X research vehicle experimental aerodynamics test program overview[J]. Journal of Spacecraft and Rockets, 2001, 38(6): 828-835.DOI: 10.2514/2.3772.

ZHU H Y, WANG G, SUN Q H, et al. Numerical evaluation on areodynamics of typical hypersonic configurations for hypersonic flight[J]. Acta Aerodynamica Sinica, 2012, 30(3): 365-372. (in Chinese)DOI: 10.3969/j.issn.0258-1825.2012.03.015.

CUI K, LI G L, XIAO Y. Aerodynamic performance study of high pressure zone capture wing configurations[C ] //33rd AIAA Applied Aerodynamics Conference, Dallas, TX. Reston, Virginia: AIAA, 2015.doi: 10.2514/6.2015-3388 .

CUI K, LI G L, XIAO Y, et al. High-pressure capturing wing configurations[J]. AIAA Journal, 2017, 55(6): 1909-1919.DOI: 10.2514/1.j055395.

CUI K, LI G L, HU S C, et al. Conceptual studies of the high pressure zone capture wing configuration for high speed air vehicles[J]. SCIENTIA SINICA Physica, Mechanica Astronomica, 2013, 43(5): 652-661. (in Chinese).DOI: 10.1360/132013-60.

TSIEN H S. Superaerodynamics, mechanics of rarefied gases[J]. Journal of the Aeronautical Sciences, 1946, 13(12): 653-664.DOI: 10.2514/8.11476.

沈青. 稀薄气体动力学[M]. 北京: 国防工业出版社, 2003.

孙泉华, 樊菁, 刘宏立, 等. 稀薄气体效应对高速飞行器气动性能的影响[C]//第一届高超声速科技学术会议论文集, 2008: 14-19.

WANG H X, LI G L, XU Y Z, et al. Preliminary study on transonic flow characteristics of a high-pressure capturing wing configuration[J]. Acta Aerodynamica Sinica, 2020, 38(3): 441-447. (in Chinese).DOI: 10.7638/kqdlxxb-2019.0075.

LI G L, CUI K, XU Y Z, et al. Experimental investigation of a hypersonic I-shaped configuration with a waverider compression surface[J]. Science China Physics, Mechanics Astronomy, 2020, 63(5): 1-3.DOI: 10.1007/s11433-019-1487-7.

LIANG J, LI Z H, LI Q, et al. Numerical simulation of aerodynamic and trim characteristics across different flow regimes for reentry module[J]. Acta Aerodynamica Sinica, 2018, 36(5): 848-855. (in Chinese).DOI: 10.7638/kqdlxxb-2018.0128.

MOSS J, BOYLES K, GREENE F. Orion aerodynamics for hypersonic free molecular to continuum conditions[C ] //Proc of the 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, Canberra, Australia. Reston, Virginia: AIAA, 2006.doi: 10.2514/6.2006-8081 .

MOSS J, GLASS C, GREENE F. DSMC simulations of Apollo capsule aerodynamics for hypersonic rarefied conditions[C ] //Proc of the 9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, San Francisco, California. Reston, Virginia: AIAA, 2006.doi: 10.2514/6.2006-3577 .

BIRD G A. Molecular gas dynamics and the direct simulation of gas flows[M]. Oxford: Clarendon press, 1994.

ZHANG J, JOHN B, PFEIFFER M, et al. Particle-based hybrid and multiscale methods for nonequilibrium gas flows[J]. Advances in Aerodynamics, 2019, 1(1): 1-15.DOI: 10.1186/s42774-019-0014-7.

FEI F, ZHANG J, LIU Z H. Multi-scale stochastic particle method based on kinetic models[J]. Acta Aerodynamica Sinica, 2019, 37(5): 731-739. (in Chinese).DOI: 10.7638/kqdlxxb-2018.0164.

FEI F, ZHANG J, LI J, et al. A unified stochastic particle Bhatnagar-Gross-Krook method for multiscale gas flows[J]. Journal of Computational Physics, 2020, 400: 108972.DOI: 10.1016/j.jcp.2019.108972.

LOFTHOUSE A J, BOYD I D, WRIGHT M J. Effects of continuum breakdown on hypersonic aerothermodynamics[J]. Physics of Fluids, 2007, 19(2): 027105.DOI: 10.1063/1.2710289.

XIAO H, WU D Y, LIU Z X, et al. Aerodynamic performance simulation of hypersonic waverider in near space[J]. Acta Armamentarii, 2009, 30(7): 907-910. (in Chinese)DOI: 10.3321/j.issn: 1000-1093.2009.07.012.

ZHANG J, ÖNSKOG T. Langevin equation elucidates the mechanism of the Rayleigh-Bénard instability by coupling molecular motions and macroscopic fluctuations[J]. Physical Review E, 2017, 96(4-1): 043104.DOI: 10.1103/physreve.96.043104.

ZHANG J, TIAN P, YAO S Q, et al. Multiscale investigation of Kolmogorov flow: From microscopic molecular motions to macroscopic coherent structures[J]. Physics of Fluids, 2019, 31(8): 082008.DOI:10.1063/1.5116206.

LI G L, CUI K, XIAO Y, et al. The design method research for the position of high pressure capturing wing[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(3): 576-584. (in Chinese).DOI: 10.6052/0459-1879-15-391.

PLIMPTON S J, MOORE S G, BORNER A, et al. Direct simulation Monte Carlo on petaflop supercomputers and beyond[J]. Physics of Fluids, 2019, 31(8): 086101.DOI: 10.1063/1.5108534.

MOSS J N, BIRD G A. Direct simulation Monte Carlo simulations of hypersonic flows with shock interactions[J]. AIAA Journal, 2005, 43(12): 2565-2573.DOI: 10.2514/1.12532.

KLOTHAKIS A G, NIKOLOS I K, KOEHLER T P, et al. Validation simulations of the DSMC code SPARTA[C ] //AIP Conference Proceedings, 2016, 1786: 050016.doi: 10.1063/1.4967566 .

OCT-1976. US Standard Atmosphere[S]. NASA TM X 1976-74335. Washington D C: National Aeronautics And SpaceAdministration, 1976.

PADILLA J F, BOYD I D. Assessment of gas-surface interaction models for computation of rarefied hypersonic flow[J]. Journal of Thermophysics and Heat Transfer, 2009, 23(1): 96-105.DOI: 10.2514/1.36375.

MEHTA P M, WALKER A, MCLAUGHLIN C A, et al. Comparing physical drag coefficients computed using different gas-surface interaction models[J]. Journal of Spacecraft and Rockets, 2014, 51(3): 873-883.DOI: 10.2514/1.A32566.

LIANG T F, LI Q, YE W J. A physical-based gas-surface interaction model for rarefied gas flow simulation[J]. Journal of Computational Physics, 2018, 352: 105-122.DOI: 10.1016/j.jcp.2017.08.061.

MEHTA N A, LEVIN D A. Molecular-dynamics-derived gas-surface models for use in direct-simulation Monte Carlo[J]. Journal of Thermophysics and Heat Transfer, 2017, 31(4): 757-771.DOI: 10.2514/1.T4934.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Influence of rarefied gas effect on the computation of heat flux

Parametric construction of blade leading and trailing edges with arbitrary central angles using NURBS curves

Influence of windbreak distance on the aerodynamic performance of high-speed trains by large eddy simulation

Molecular dynamics simulation of gas-solid interaction on the surface of ultra-low orbit spacecraft

Research progress on Reynolds number effects in the design of large aircraft

Related Author

ZHANG Jiaqi

OU Jihui

CHEN Jie

CHEN Jianjun

XIA Yifan

XU Jingchao

NI Haonan

YANG Yonggang

Related Institution

Laboratory for High Speed Aerodynamics, School of Mechanical Engineering, Tianjin University

School of Aeronautics and Astronautics, Zhejiang University, Hangzhou

School of Mechanical and Electrical Engineering, Lanzhou Jiaotong University, Lanzhou

China Academy of Aerospace Aerodynamics, Beijing

National Key Laboratory of Aircraft Configuration Design, Xi'an

AI问答

⁰