The heat reduction performance at sharp leading edges of an X-51A-like aircraft with porous counterflowing jet

ZHOU Lang; XU Chunguang

doi:10.13471/j.cnki.acta.snus.2022B038

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The heat reduction performance at sharp leading edges of an X-51A-like aircraft with porous counterflowing jet

Research articles | 更新时间：2023-11-01

- The heat reduction performance at sharp leading edges of an X-51A-like aircraft with porous counterflowing jet
- Acta Scientiarum Naturalium Universitatis Sunyatseni Vol. 62, Issue 2, Pages: 156-164(2023)
- 作者机构：
  
  中山大学航空航天学院，广东深圳 518107
- 作者简介：
- 基金信息：
- DOI：10.13471/j.cnki.acta.snus.2022B038
  CLC： V411
- Published：25 March 2023，
  
  Published Online：20 October 2022，
  
  Received：17 April 2022，
  
  Accepted：23 May 2022
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周朗,徐春光.类X-51A飞行器尖锐前缘多孔逆向喷流降热[J].中山大学学报(自然科学版),2023,62(02):156-164.

ZHOU Lang,XU Chunguang.The heat reduction performance at sharp leading edges of an X-51A-like aircraft with porous counterflowing jet[J].Acta Scientiarum Naturalium Universitatis Sunyatseni,2023,62(02):156-164.
周朗,徐春光.类X-51A飞行器尖锐前缘多孔逆向喷流降热[J].中山大学学报(自然科学版),2023,62(02):156-164. DOI： 10.13471/j.cnki.acta.snus.2022B038.

ZHOU Lang,XU Chunguang.The heat reduction performance at sharp leading edges of an X-51A-like aircraft with porous counterflowing jet[J].Acta Scientiarum Naturalium Universitatis Sunyatseni,2023,62(02):156-164. DOI： 10.13471/j.cnki.acta.snus.2022B038.

摘要

采用三维N-S方程和SST

k-ω

湍流模型，对类X-51A飞行器尖锐前缘多孔逆向喷流流场进行了数值模拟。利用文献实验模型，对数值模拟方法的准确性进行了验证。在此基础上，对不同孔径、孔距和喷孔扩张角下，逆向喷流的降热机理和效果进行了分析。结果表明，在多孔逆向喷流配置合适的情况下，会显著改变飞行器前缘流场结构，能有效降低飞行器前缘热流。随着喷孔扩张角和孔径的增加，降热效果有所提升；随着喷孔直径的减小，降热性能降低。此外，建立了孔径和孔距的关联参数，发现在孔径与孔距比值一定时，孔径越小，降热性能越好。

Abstract

We carried out numerical simulations of the flow field of the sharp leading edges of an X-51A-like aircraft using the three-dimensional Navier-Stokes(N-S) equations and the SST

k-ω

turbulence model after verifying the accuracy of the numerical simulation method by comparing it with the experimental data from the published literature. On this basis

we analyzed the heat reduction mechanism and effect of the sharp leading edges with the porous counterflowing jet under different jet exit sizes

jet pitches

and jet expansion angles. The results show that the configuration of the porous counterflowing jet significantly affects the flow field at the leading edge of the vehicle and proper configurations can effectively reduce the heat. Increasing the jet pitch reduces the heat flux of the sharp leading edges; enlarging the jet exit size and jet expansion angle brings similar effects. Moreover

for the same parameter

which is the ratio of jet pitch and exit size

the smaller the exit size of the counterflowing jet

the more heat reduction.

关键词

高超声速降热多孔逆向喷流尖锐前缘

Keywords

hypersonicheat reductionporouscounterflowing jetsharp leading edges

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