Airworthiness compliance verification of aerodynamic flowfield of a large-scale icing wind tunnel

GUO Xiangdong; LIU Qinglin; LAI Qingren; YANG Shengke; ZHAO Zhao

doi:10.7638/kqdlxxb-2019.0086

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Airworthiness compliance verification of aerodynamic flowfield of a large-scale icing wind tunnel

更新时间：2026-05-28

- Airworthiness compliance verification of aerodynamic flowfield of a large-scale icing wind tunnel
- Vol. 39, Issue 2, Pages: 184-195(2021)
- 作者机构：
  
  中国空气动力研究与发展中心结冰与防除冰重点实验室,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0086
  CLC： V228.7+1
- Published：2021
- 稿件说明：
移动端阅览
郭向东, 柳庆林, 赖庆仁, 等. 大型结冰风洞气流场适航符合性验证[J]. 空气动力学学报, 2021, 39(2): 184−195.

GUO Xiangdong, LIU Qinglin, LAI Qingren, et al. Airworthiness compliance verification of aerodynamic flowfield of a large-scale icing wind tunnel[J]. 2021, 39(2): 184-195.
郭向东, 柳庆林, 赖庆仁, 等. 大型结冰风洞气流场适航符合性验证[J]. 空气动力学学报, 2021, 39(2): 184−195. DOI： 10.7638/kqdlxxb-2019.0086

GUO Xiangdong, LIU Qinglin, LAI Qingren, et al. Airworthiness compliance verification of aerodynamic flowfield of a large-scale icing wind tunnel[J]. 2021, 39(2): 184-195. DOI： 10.7638/kqdlxxb-2019.0086.

摘要

大型结冰风洞气流场适航符合性是大型结冰风洞适航应用的先决条件。为验证3 m × 2 m结冰风洞气流场适航符合性，首先建立了结冰风洞气流场适航符合性验证方法，然后针对主试验段构型，开展了气流场适航符合性验证试验，考察了试验段气流速度和喷嘴干空气射流对流场特征参数（气流速度、气流偏角和气流湍流度）的影响，最后评估了试验段内气流场品质，获得了结冰风洞气流场控制包线。结果表明：喷雾耙结构会影响试验段内气流速度和气流偏角空间分布形态，进而导致了非均匀峰值区的形成；增大试验段气流速度会改善气流场品质，但喷嘴干空气射流会显著恶化试验段气流速度低于60 m/s的气流场品质；3 m × 2 m结冰风洞主试验段气流场品质在主要试验速度范围内均满足适航审定要求。

Abstract

The airworthiness compliance of the aerodynamic flowfield is the precondition for the airworthiness application of large icing wind tunnels. In order to verify the airworthiness compliance of the aerodynamic flowfield of the 3 m × 2 m icing wind tunnel at China Aerodynamic Research and Development Center (CARDC)

a verification method is established first in the present study. Then

a verification test is conducted for the main test section of the icing wind tunnel

where influences of the flow velocity and the dry air nozzel jet on characteristic parameters of the flowfield (the airspeed

the flow angularity and the turbulence intensity) are examined. The quality of the aerodynamic flowfield is evaluated

with the aerodynamic operating envelop obtained. Results show that the spray bar configuration has great effects on the spatial distribution of the airspeed and the flow angularity in the test section

resulting in the formation of a non-uniform peak area. Increasing the flow velocity at the test section can improve the quality of the aerodynamic flowfield

but such an improment can be significantly worsened by the nozzle dry air jet when the flow velocity at the test section is below 60 m/s. It is concluded that the quality of the aerodynamic flowfield in the main test section of the 3 m × 2 m icing wind tunnel at CARDC meets the requirement of the airworthiness certification in the main testing airspeed range.

关键词

Keywords

references

DU Y X, LI M, GUI Y W, et al. Review of thermodynamic behaviors in aircraft icing process[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2): 25-36. (in Chinese) DOI: 10.7527/S1000-6893.2016.0277

YI X, WANG B, LI W B, et al. Research progress on ice shape measurement approaches for aircraft icing[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2): 13-24 (in Chinese). DOI: 10.7527/S1000-6893.2016.0276

GUO X D, WANG Z X, LI M, et al. Numerical study of super-cooling characteristics of droplet in icing wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(10): 121254. (in Chinese) DOI: 10.7527/S1000-6893.2017.121254

WANG Z X, SHEN H, GUO L, et al. Cloud calibration method of 3m×2m icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(2): 61-67. (in Chinese) DOI: 10.11729/syltlx20170163

IRVINE T, KEVDZIJA S, SHELDON D, et al. Overview of the icing and flow quality improvements program for the NASA-Glenn Icing Research Tunnel[C ] // 39th Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virigina: AIAA, 2001. doi: 10.2514/6.2001-229

GONSALEZ J, ARRINGTON E, CURRY M. Quality surveys of the NASA Glenn icing research tunnel (2000 tests)[C ] // 39th Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virigina: AIAA, 2001. doi: 10.2514/6.2001-232

GONSALEZ J, ARRINGTON E, CURRY M. Thermal calibration of the NASA Glenn icing research tunnel (2000 tests)[C ] // 39th Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virigina: AIAA, 2001. doi: 10.2514/6.2001-233

BHARGAVA C, LOTH E, POTAPCZUK M. Aerodynamic simulations of the NASA Glenn icing research tunnel[C ] // 41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2003. doi: 10.2514/6.2003-566

PASTOR-BARSI C, ARRINGTON A. Aero-thermal calibration of the NASA Glenn icing research tunnel (2012 test)[C ] // 4th AIAA Atmospheric and Space Environments Conference, New Orleans, Louisiana. Reston, Virigina: AIAA, 2012. doi: 10.2514/6.2012-2934

STEEN L C, VAN ZANTE J, BROEREN A, et al. Flow quality surveys in the settling chamber of the NASA Glenn icing research tunnel (2011 tests)[C ] // 4th AIAA Atmospheric and Space Environments Conference, New Orleans, Louisiana. Reston, Virigina: AIAA, 2012. doi: 10.2514/6.2012-2935

CLARK K, MALINOWSKI M, LOTH E, et al. Air flow and liquid water concentration simulations of the 2012 NASA Glenn icing research tunnel[C ] // 4th AIAA Atmospheric and Space Environments Conference, New Orleans, Louisiana. Reston, Virginia: AIAA, 2012. doi: 10.2514/6.2012-2936

VECCHIONE L, DE MATTEIS P. An overview of the CIRA icing wind tunnel[C ] // 41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2003. doi: 10.2514/6.2003-900

ESPOSITO B M, RAGNI A, FERRIGNO F, et al. Cloud calibration update of the CIRA icing wind tunne: 2003-01-2132[R].SAE Technical Paper, 2003.

IRANI E, AL-KHALIL K. Calibration and recent upgrades to the Cox icing wind tunnel[C]// 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008.

FU C, PENG Q, LI X F, et al. Five-hole flow angle probe calibration and measurement in subsonic flow[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(3): 88-90.

Ac-9c Aircraft Icing Technology Committee. Calibration and acceptance of icing wind tunnels: SAE ARP-5905 [S]. 2009.

GONSALEZ J C, ARRINGTON E A. Five-hole flow angle probe calibration for the NASA Glenn Icing Research Tunnel[C]//19th AIAA Advanced Measurement and Ground Testing Technology Conference, 1996.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Investigation and application of ice accretion shape online measurement system for large-scale icing wind tunnel

Numerical simulation of droplet deformation in uniform airflow

Icing prediction method for arbitrary airfoil using deep neural networks

New progress of 3 m × 2 m icing wind tunnel test technology from 2020 to 2022

A hybrid scaling method for icing wind tunnel and validation

Related Author

YI Xian

CHENG Zhihang

LIU Guanmian

SUN Dongning

WEI Longtao

MA Jun

ZUO Chenglin

ZHAO Ning

Related Institution

Icing and Anti/De-icing Key Lab, China Aerodynamics Research and Development Center, Mianyang

AVIC General Huanan Aircraft Industry Co., Ltd., Zhuhai

College of Aerospace Engineering, Nanjing University of Aeronautics And Astronautics, Nanjing

State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing

School of Computer Science, Southwest Petroleum University, Chengdu

AI问答

⁰