空气动力学学报2024，Vol.42Issue(11)：43-54,12.DOI:10.7638/kqdlxxb-2023.0130
不同外罩型线短舱边界层的转捩位置预测
Transition prediction of boundary layers over an engine nacelle with different outer covers
文豪 1苏彩虹 2张美红 3刘凯礼 4王美黎4
作者信息
- 1. 北京空天技术研究所,北京 100074
- 2. 天津大学机械工程学院,天津 300072
- 3. 中国商用飞机有限责任公司上海飞机设计研究院,上海 201210||西北工业大学航空学院,西安 710072
- 4. 中国商用飞机有限责任公司上海飞机设计研究院,上海 201210
- 折叠
摘要
Abstract
In the design of the nacelle outer cover profile,it is crucial to maintain the boundary layer's laminar state to minimize wall friction and enhance payload capacity.Understanding the boundary-layer transition mechanisms and accurately predicting the transition front is fundamental to effectively evaluate different designs of the nacelle.In this work,we focus on the stability characteristics of boundary layers over nacelle with three different outer covers under cruise conditions.Considering transition mechanisms correlated with the T-S waves and the shock wave-induced separation bubbles,the transition fronts are predicted.The results indicate that as the unfavorable pressure gradient increases,T-S waves become more unstable,leading to earlier boundary-layer separation.Therefore,maintaining a relatively large range of favourable pressure gradient as well as reducing unfavorable pressure gradient will delay the boundary-layer transition.In addition,for a scaled nacelle model,the predicted transition front and that obtained in wind tunnel tests are morphologically similar,confirming the validity of the prediction method.关键词
转捩预测/短舱/边界层/线性稳定性理论/eN方法Key words
transition prediction/nacelle/boundary layer/liner stability theory/eNmethod分类
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文豪,苏彩虹,张美红,刘凯礼,王美黎..不同外罩型线短舱边界层的转捩位置预测[J].空气动力学学报,2024,42(11):43-54,12.
