Fast transition prediction for wind tunnel testing of the transonic natural laminar flow standard model CRM-NLF

LIU Yinhui; WU Dongrun; DU Xi; LIN Dakai

doi:10.7638/kqdlxxb-2022.0035

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Fast transition prediction for wind tunnel testing of the transonic natural laminar flow standard model CRM-NLF

更新时间：2026-05-28

- Fast transition prediction for wind tunnel testing of the transonic natural laminar flow standard model CRM-NLF
- Vol. 41, Issue 7, Pages: 36-47(2023)
- 作者机构：
  
  1. 中国商用飞机有限责任公司北京民用飞机技术研究中心,北京,102211
  2. 民用飞机设计数字仿真技术北京市重点实验室,北京,102211
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0035
  CLC： V211.4
- Published：2023
- 稿件说明：
移动端阅览
刘银辉, 吴东润, 杜玺, 等. 跨声速自然层流标模CRM-NLF风洞试验快速转捩预测[J]. 空气动力学学报, 2023, 41(7): 36−47.

LIU Yinhui, WU Dongrun, DU Xi, et al. Fast transition prediction for wind tunnel testing of the transonic natural laminar flow standard model CRM-NLF[J]. 2023, 41(7): 36-47.
刘银辉, 吴东润, 杜玺, 等. 跨声速自然层流标模CRM-NLF风洞试验快速转捩预测[J]. 空气动力学学报, 2023, 41(7): 36−47. DOI： 10.7638/kqdlxxb-2022.0035

LIU Yinhui, WU Dongrun, DU Xi, et al. Fast transition prediction for wind tunnel testing of the transonic natural laminar flow standard model CRM-NLF[J]. 2023, 41(7): 36-47. DOI： 10.7638/kqdlxxb-2022.0035.

摘要

中国商飞北研中心开发了快速CFD分析工具CFAST进行层流基本流场计算，单工况的计算时间仅为200 s，然后耦合转捩预测模块进行转捩预测分析，大幅缩减了计算周期，从而实现跨声速民机典型后掠机翼三维边界层的快速转捩预测。转捩预测模块基于线性稳定性理论的双e

方法，可以同时考虑横流驻波不稳定模态和Tollmien-Schlichting波不稳定模态对转捩的影响。目前，公开的跨声速高雷诺数民机自然层流试验数据十分稀缺，本文以NASA公开的跨声速高雷诺数自然层流标模CRM-NLF为研究对象，研究了迎角、雷诺数和马赫数对转捩的影响。计算结果与试验结果以及基于RANS的转捩计算结果吻合很好，说明开发的快速转捩预测工具高效可靠，可以用于跨声速民机层流机翼设计和优化。

Abstract

The design procedure of transonic natural laminar wings can benefit significantly from efficient transition prediction software capable of handling complex aerodynamic geometries. In this article

Commercial Aircraft Corporation of China Ltd (COMAC) Beijing Aircraft Technology Research Institute developed a Computational Fluid Dynamics software CFAST to obtain laminar base flows. CFAST is highly efficient; it only costs 200 seconds per case. The output of CFAST is then integrated into a transition prediction module to perform fast transition prediction of three-dimensional transonic back-swept wing boundary layers. The transition

prediction module adopts the dual-e

criterion from the linear stability theory so that both Tollmien-Schlichting and stationary crossflow modes can be considered. Since open-source experimental data of high-Reynolds-number laminar flows are rare

the standard research model CRM-NLF designed by NASA is utilized to study the effects of the attack angle

Reynolds number

and Mach number on the transition prediction. The transition prediction results agree well with those obtained by RANS with transition models

suggesting that the method is of great potential in designing and optimizing of transonic natural laminar wings.

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Keywords

references

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