壁面催化效应对高超声速气动热影响研究

周凯; 朱晓军; 欧东斌; 胡宗民; 姜宗林; 牟乾辉

doi:10.7638/kqdlxxb-2018.0130

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壁面催化效应对高超声速气动热影响研究

研究论文 | 更新时间：2026-05-28

- 壁面催化效应对高超声速气动热影响研究
- Wall catalytic effects on aerodynamic heat of hypersonic flow
- 空气动力学学报 2020年38卷第4期页码：660-667
- 作者机构：
  
  1. 中国航天空气动力技术研究院,北京,100074
  2. 中国科学院力学研究所,北京,100190
  3. 中国科学院大学工程科学学院,北京,100049
- 作者简介：
  
  周凯(1989-), 男, 河南新乡人, 工程师, 研究方向:超高声速气动热.E-mail:zkxzh@mail.ustc.edu.cn
  胡宗民(1970-), E-mail:huzm@imech.ac.cn
- 基金信息：
  
  国家自然科学基金（11672308，11532014）
- DOI：10.7638/kqdlxxb-2018.0130
  中图分类号： V211.3
- 纸质出版：2020
- 稿件说明：
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周凯, 朱晓军, 欧东斌, 胡宗民, 姜宗林, 牟乾辉. 壁面催化效应对高超声速气动热影响研究[J]. 空气动力学学报, 2020, 38(4): 660-667.

ZHOU Kai, ZHU Xiaojun, OU Dongbin, et al. Wall catalytic effects on aerodynamic heat of hypersonic flow[J]. 2020, 38(4): 660-667.
周凯, 朱晓军, 欧东斌, 胡宗民, 姜宗林, 牟乾辉. 壁面催化效应对高超声速气动热影响研究[J]. 空气动力学学报, 2020, 38(4): 660-667. DOI： 10.7638/kqdlxxb-2018.0130.

ZHOU Kai, ZHU Xiaojun, OU Dongbin, et al. Wall catalytic effects on aerodynamic heat of hypersonic flow[J]. 2020, 38(4): 660-667. DOI： 10.7638/kqdlxxb-2018.0130.

摘要

高超声速飞行器壁面催化效应会导致激波层中原子在壁面处复合释热，加剧周围气动热环境。针对高超声速流动壁面催化特性，选择不同飞行马赫数及高度条件，采用完全催化和非催化两种条件对球锥模型壁面热流率进行数值模拟计算，研究壁面催化效应对气动热的影响规律。结果表明，固定飞行高度时，壁面催化效应对气动热的影响随马赫数增加而加强，

=25条件下驻点处完全催化与非催化热流比值高达1.92；固定飞行马赫数时，在50 km高空以上壁面催化效应对气动热的影响随高度增加而减弱；壁面催化效应不仅会影响壁面附近的流场特性及组分分布状态，而且对整个激波层都有一定的影响作用。

Abstract

The wall catalytic activity of hypersonic vehicles leads the atoms produced in the shock layer recombined at the body surface

leaving the recombination energy and increasing the aerodynamic heat there. To study this crucial item

the non-catalytic and fully catalytic wall conditions are applied in the numerical simulation to calculate the heat flux on a sphere-cone model

basing on different flight Mach numbers and altitude conditions. The research indicates that the wall catalytic effects on heat flux enhance as the Mach numbers increase. The heat flux ratio of the stagnant point on account of fully catalytic versus non-catalytic wall conditions reaches up to 1.92 at Mach number 25. However

this effect tends to be weaken if the altitude increases beyond 50 km with a same flight Mach number. What is more

the wall catalytic activity can influence the flow features and species distribution inside of the whole shock layer

not just around the wall surface.

关键词

Keywords

references

ANDERSON J D. Hypersonic and high temperature gas dynamics[M]. AIAA, 2000:449-499.

GOULARD R J. On catalytic recombination rates in hypersonic stagnation heat transfer[J]. Jet Propulsion, 1958, 28(11):737-745.

INGERI G R. Nonequilibrium hypersonic stagnation flow with arbitrary surface catalycity including low Reynolds number effects[J]. International Journal of Heat and Mass Transfer, 1966, 9(8):755-772.

STEWART D A. Surface catalysis and characterization of proposed candidate TPS for access-to-space vehicles: NASA TM-112206[R]. Moffett Field: NASA, 1997.

SCOTT C D. Catalytic recombination of nitrogen and oxygen on high-temperature reusable surface insulation: AIAA-80-1477[R]. Snowmass: AIAA, 1980.

STEWART D, RAKICH J, LANFRANCO M. Catalytic surface effects experiment on the space shuttle: AIAA-81-1143[R]. Palo Alto: AIAA, 1981.

POST S L. Space shuttle case studies: Challenger and Columbia[C]//Proceeding of 121st ASEE Annual Conference Exposition. Indianapolis: American Society for Engineering Education, 2014: 8419.

MACLEAN M, WADHANMS T, HOLDEN M, et al. Integration CFD and experiments in the CUBRC LENS shock tunnel facilities to understand the physics of hypersonic and hypervelocity flows[C]//Proceeding of 4th Symposium on integrating CFD and experiments in aerodynamics. Belgium: von Karman Institute, 2009.

HORNUNG H G. Ground testing for hypervelocity flow, capabilities and limitations, RTO-EN-AVT-186[R]. Pasadena: California Institute of Technology, 2010.

BERTIN JJ, CUMMINGS R M. Critical hypersonic aerothermodynamic phenomena[J]. Annual Review of Fluid Mechanics, 2006, 38:129-157.

BARBATO M, GIORDANO D, MUYLAERT J, et al. Comparison of catalytic wall conditions for hypersonic flow[J]. Journal of spacecraft and rockets, 1996, 33(5):620-627.

MACLEAN M, HOLDEN M. Numerical assessment of data in catalytic and transitional flows for Martian entry, AIAA-2006-2946[R]. San Francisco: AIAA, 2006.

MACLEAN M, HOLDEN M. Catalytic effects on heat transfer measurements for aerothermal studies with CO 2 : AIAA-2006-182[R ] . Reno: AIAA, 2006.

CAPITELLI M, DEVOTO R S. Transport coefficients of high-temperature nitrogen[J]. The Physics of Fluids, 1973, 16(11):1835-1841.

PARK C. Review of chemical-kinetic problems of future NASA mission, I:earth entries[J]. Journal of Thermophysics and Heat Transfer, 1993, 7(3):385-398.

KIM K H, KIM C, RHO O H. Methods for the accurate computations of hypersonic flows I:AUSMPW+ scheme[J]. Journal of computational physics, 2001, 174(1):38-80.

KIM K H, KIM C, RHO O H. Accurate computations of hypersonic flows using AUSMPW+ scheme and shock-aligned grid technique: AIAA-98-2442[R]. Seoul: AIAA, 1998.

DIM K H, LEE J H, RHO O H. An improvement of AUSM schemes by introducing the pressure-based weight function[J]. Computers Fluids, 1998, 27(3):311-346.

WIETING A R, HOLDEN M S. Experimental shock-wave interference heating on a cylinder at Mach 6 and 8[J]. Aiaa Journal, 1989, 27(11):1557-1565.

MUYLAERT J, WALPOT L, HAUSER J. Standard model testing in the European high enthalpy facility F4 and extrapolation to flight: AIAA-92-3905[R]. Nashville: AIAA, 1992.

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