2.4 m连续式跨声速风洞气动设计与研究

张刃; 杜文天; 李庆利; 崔晓春

doi:10.7638/kqdlxxb-2022.0185

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2.4 m连续式跨声速风洞气动设计与研究

研究专栏——特种风洞研制与应用 | 更新时间：2026-05-28

- 2.4 m连续式跨声速风洞气动设计与研究
- Aerodynamic design of 2.4 m continuous transonic wind tunnel
- 空气动力学学报 2023年41卷第1期页码：22-38
- 作者机构：
  
  1. 中国航空工业空气动力研究院,沈阳,110034
  2. 高速高雷诺数气动力航空科技重点实验室,沈阳,110034
- 作者简介：
  
  张刃（1985-），男，辽宁大连人，高级工程师，研究方向：试验空气动力学. E-mail：zr8526@163.com
  杜文天*（1988-）男，高级工程师，研究方向：试验空气动力学. E-mail：408182824@qq.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0185
  中图分类号： V211.74+1
- 纸质出版：2023
- 稿件说明：
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张刃, 杜文天, 李庆利, 等. 2.4 m连续式跨声速风洞气动设计与研究[J]. 空气动力学学报, 2023, 41(1): 22−38.

ZHANG Ren, DU Wentian, LI Qingli, et al. Aerodynamic design of 2.4 m continuous transonic wind tunnel[J]. 2023, 41(1): 22-38.
张刃, 杜文天, 李庆利, 等. 2.4 m连续式跨声速风洞气动设计与研究[J]. 空气动力学学报, 2023, 41(1): 22−38. DOI： 10.7638/kqdlxxb-2022.0185

ZHANG Ren, DU Wentian, LI Qingli, et al. Aerodynamic design of 2.4 m continuous transonic wind tunnel[J]. 2023, 41(1): 22-38. DOI： 10.7638/kqdlxxb-2022.0185.

摘要

连续式跨声速风洞由轴流压缩机驱动运行，具有运行范围宽、流场品质高、运行时间长等优点，是国际上最主要的跨声速风洞类别。近年来我国飞行器型号研制对大型连续式跨声速风洞的试验需求快速增长，为了弥补我国大型连续式跨声速风洞设备短板，中国航空工业空气动力研究院建设了2.4 m连续式跨声速风洞，该风洞是我国第一座大型连续式跨声速风洞。为了获得最佳的风洞流场品质和气动性能，航空工业气动院研发了多项适用于连续式跨声速风洞的气动外形设计技术，包括风洞的喷管、试验段、二喉道等高速部段的气动设计技术和低速部段气动设计技术。本文详细介绍了连续式跨声速风洞的总体设计要求和主要部段的气动设计方法，并通过CFD计算和风洞试验开展研究与验证。通过应用先进风洞气动设计技术指导风洞建设及调试，2.4 m连续式跨声速风洞的流场均匀性、噪声和湍流度已达到国际先进水平，试验数据品质与国际先进风洞一致。

Abstract

Driven by axial flow compressor

the continuous transonic wind tunnel has the advantages of wide operating range

high flow field quality and long running time

and is the most important type of transonic wind tunnel in the world. In recent years

the test demand of large continuous transonic wind tunnels for the aircraft development in China is growing rapidly

therefore

the AVIC Aerodynamics Research Institute (AVICARI) built the first continuous transonic wind tunnel of China

i.e. the 2.4 m continuous transonic wind tunnel. In order to obtain the best flow field quality and aerodynamic performance of the wind tunnel

AVICARI has developed a number of aerodynamic design techniques applicable to continuous transonic wind tunnels

including design methods for high-speed sections

such as the nozzle

the test section

the second throat

as well as techniques for the low-speed sections. In this paper

both the overall design requirement and the aerodynamic design methods of some main sections suitable for continuous transonic wind tunnels are introduced in detail

which are studied and verified by CFD and wind tunnel tests. Through the application of these aerodynamic design techniques

the flow field uniformity

noise level and turbulence intensity of the 2.4 m continuous transonic wind tunnel have reached the international advanced level

with the test data in good consistency with those from similar wind tunnels abroad.

关键词

Keywords

references

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