壁面质量引射对高速飞行器减阻降热影响的研究

朱广生; 段毅; 姚世勇; 范月华

doi:10.7638/kqdlxxb-2023.0136

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壁面质量引射对高速飞行器减阻降热影响的研究

研究专栏——庆祝国防科技大学建校70周年 | 更新时间：2026-05-28

- 壁面质量引射对高速飞行器减阻降热影响的研究
- Effects of wall mass injection on drag and heat reduction characteristics of high-speed flight vehicles
- 空气动力学学报 2023年41卷第8期页码：59-70
- 作者机构：
  
  1. 中国运载火箭技术研究院,北京,100076
  2. 中国运载火箭技术研究院空间物理重点实验室,北京,100076
- 作者简介：
  
  朱广生（1963-），男，江苏沛县人，博士，研究方向：飞行器总体与气动设计
  姚世勇*（1986-），高级工程师，研究方向：高速空气动力学. E-mail： shiyong-yao@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0136
  中图分类号： V211
- 纸质出版：2023
- 稿件说明：
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朱广生, 段毅, 姚世勇, 等. 壁面质量引射对高速飞行器减阻降热影响的研究[J]. 空气动力学学报, 2023, 41(8): 59−70.

ZHU Guangsheng, DUAN Yi, YAO Shiyong, et al. Effects of wall mass injection on drag and heat reduction characteristics of high-speed flight vehicles[J]. 2023, 41(8): 59-70.
朱广生, 段毅, 姚世勇, 等. 壁面质量引射对高速飞行器减阻降热影响的研究[J]. 空气动力学学报, 2023, 41(8): 59−70. DOI： 10.7638/kqdlxxb-2023.0136

ZHU Guangsheng, DUAN Yi, YAO Shiyong, et al. Effects of wall mass injection on drag and heat reduction characteristics of high-speed flight vehicles[J]. 2023, 41(8): 59-70. DOI： 10.7638/kqdlxxb-2023.0136.

摘要

针对未来新型高速飞行器高升阻比和低热载荷的发展需求，本文选取贴近工程实际应用的三角翼为研究对象，开展了飞行状态下大面积壁面质量引射对减阻降热影响的数值模拟研究，对比分析了壁面质量引射在不同的飞行高度、来流马赫数、引射流量、引射温度和气体模型条件下对三角翼气动力热特性的影响。从高速飞行器减阻降热的工程需求出发，指出了质量引射流动控制在工程应用中存在的问题与后续应重点关注的方向。

Abstract

Aiming at the development requirements of high lift-drag ratio and low thermal load of a new type of high-speed flight vehicle in the future

a large swept delta wing which is close to the practical engineering is chosen as the study object in this paper. Numerical simulations on the effects of large-area wall mass injection on the drag and heat reductions in flight states are carried out

and the influences of mass injection on the aerodynamic force and heat characteristics of delta wing under different flight altitudes

freestream Mach numbers

injection flow rates

injection temperatures and gas models are compared and analyzed. Based on the engineering requirements of drag and heat reductions of high-speed flight vehicles

the issues of wall mass injection in the engineering applications and the research directions that deserve more attention in the future are pointed out.

关键词

Keywords

references

FANG Y C, LIOU W W, XU S X. Skin friction prediction for high-speed turbulent boundary layers with ablation[J]. Journal of Spacecraft and Rockets, 2004, 41(5): 893-895. DOI: 10.2514/1.8593

HEFNER J N, BUSHNELL D M. Viscous drag reduction via surface mass injection[M]//BUSHNELL D M, HEFNER J N. , Eds. Viscous Drag Reduction in Boundary Layers. Washington DC: AIAA, 1990: 457-476. doi: 10.2514/5.9781600865978.0457.0476

HWANG D P. Skin-friction reduction by a micro-blowing technique[J]. AIAA Journal, 1998, 36: 480-481. DOI: 10.2514/3.13846

HWANG D. Review of research into the concept of the microblowing technique for turbulent skin friction reduction[J]. Progress in Aerospace Sciences, 2004, 40(8): 559-575. DOI: 10.1016/j.paerosci.2005.01.002

BATHEL B, DANEHY P, INMAN J, et al. PLIF visualization of active control of hypersonic boundary layers using blowing[C]// 26th AIAA Aerodynamic Measurement Technology and Ground Testing Conference, Seattle, Washington. Reston, Virigina: AIAA, 2008: AIAA2008-4266. doi: 10.2514/6.2008-4266

ORLIK E, FEDIOUN I, LARDJANE N. Hypersonic boundary-layer transition forced by wall injection: a numerical study[J]. Journal of Spacecraft and Rockets, 2014, 51(4): 1306-1318. DOI: 10.2514/1.a32645

CHEN Z, YU C P, LI L, et al. Effect of uniform blowing or suction on hypersonic spatially developing turbulent boundary layers[J]. Science China Physics, Mechanics Astronomy, 2016, 59(6): 664702. DOI: 10.1007/s11433-015-0511-0

CERMINARA A, DEITERDING R, SANDHAM N. Direct numerical simulation of blowing in a hypersonic boundary layer on a flat plate with slots[C]// 2018 Fluid Dynamics Conference, Atlanta, Georgia. Reston, Virginia: AIAA, 2018: AIAA2018-3713. doi: 10.2514/6.2018-3713

ZHANG Y, LIU Y, ZHANG Y, et al. Hypersonic boundary layer flow and heat transfer analysis of compressible fluid over a permeable wall with gas injection[J]. International Communications in Heat and Mass Transfer, 2021, 129: 105688. DOI: 10.1016/j.icheatmasstransfer.2021.105688

MO F, SU W, GAO Z X, et al. Numerical investigations of the slot blowing technique on the hypersonic vehicle for drag reduction[J]. Aerospace Science and Technology, 2022, 121: 107372. DOI: 10.1016/j.ast.2022.107372

KING H H, TALBOT L. Effect of mass injection on the drag of a slender cone in hypersonic flow[J]. AIAA Journal, 1964, 2(5): 836-844. DOI: 10.2514/3.2439

GAO N, NAUGHTON J, EWING D. Measurements of wall shear stress of an offset attaching planar jet with co-flow[C]// 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2006: AIAA2006-646. doi: 10.2514/6.2006-646

WINDISCH C, REINARTZ B, MUELLER S. Numerical simulation of coolant variation in laminar supersonic film cooling[C]// 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee. Reston, Virigina: AIAA, 2012: AIAA2012-949. doi: 10.2514/6.2012-949

HOWARD F, STROKOWSKI A J. Direct measurements and analysis of skin friction and cooling downstream of multiple flush-slot injection into a turbulent Mach 6 boundary layer[R]. NASA-TP-1176, 1978.

SAHOO N, KULKARNI V, SARAVANAN S, et al. Film cooling effectiveness on a large angle blunt cone flying at hypersonic speed[J]. Physics of Fluids, 2005, 17(3): 036102. DOI: 10.1063/1.1862261

KELLER M A, KLOKER M J, OLIVIER H. Influence of cooling-gas properties on film-cooling effectiveness in supersonic flow[J]. Journal of Spacecraft and Rockets, 2015, 52(5): 1443-1455. DOI: 10.2514/1.a33203

MARVIN J G, AKIN C M. Combined effects of mass addition and nose bluntness on boundary-layer transition[J]. AIAA Journal, 1970, 8(5): 857-863. DOI: 10.2514/3.5778

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