考虑巡航攻角的三维内转进气道设计与分析

郑晓刚; 胡占仓; 蔡泽君; 施崇广; 朱呈祥; 尤延铖

doi:10.7527/S1000-6893.2024.31233

航空学报 >

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DOI: https://doi.org/10.7527/S1000-6893.2024.31233

考虑巡航攻角的三维内转进气道设计与分析

郑晓刚 ,
胡占仓 ,
蔡泽君 ,
施崇广 ,
朱呈祥 ,
尤延铖

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1. 厦门大学
2. 厦门大学航空航天学院

收稿日期: 2024-09-19

修回日期: 2024-11-28

网络出版日期: 2024-11-29

基金资助

国家自然科学基金;国家自然科学基金;博士后科学基金资助项目

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Design and analysis of the 3D inward-turning inlet under the cruising angle of attack

ZHENG Xiao-Gang ,
HU Zhan-Cang ,
CAI Ze-Jun ,
SHI Chong-Guang ,
ZHU Cheng-Xiang ,
YOU Yan-Cheng

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Received date: 2024-09-19

Revised date: 2024-11-28

Online published: 2024-11-29

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摘要

头部进气的吸气式高超声速飞行器巡航状态多保持特定攻角飞行，导致常规不考虑攻角设计的三维内转进气道长时间工作于非设计攻角下，进气道性能下降明显。为此，将局部偏转吻切方法由外流进一步拓展至内流，提出了考虑巡航攻角的三维内转进气道设计方法。该方法将内转进气道分成激波决定段与压力分布决定段两部分，通过同时指定入射激波曲面和各流面内沿程压力分布，实现了给定来流攻角条件下的全三维内收缩流动的快速逆向求解。研究结果表明，基于该方法设计的进气道能够在巡航攻角下较为精准的复现预设计激波与内收缩流场，进气道激波封口特性良好，实现全流量捕获。与常规不考虑攻角设计的进气道相比，考虑攻角设计的内转进气道在保证压缩性能基本一致的情况下，无黏流量捕获系数提升1.94%，喉道处无黏总压恢复系数提升6.56%。考虑粘性后，流量捕获系数提升1.90%，喉道处总压恢复系数提升6.69%，而隔离段出口的总压恢复系数则提升7.13%。

关键词： 高超声速; 内转进气道; 巡航攻角; 流量捕获; 总压恢复

本文引用格式

郑晓刚 , 胡占仓 , 蔡泽君 , 施崇广 , 朱呈祥 , 尤延铖 . 考虑巡航攻角的三维内转进气道设计与分析[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2024.31233

Abstract

Air-breathing hypersonic vehicles with a head intake system typically cruise at a specific angle of attack for higher lift-to-drag characteristics. However, it can cause the 3D inward-turning inlet, designed without considering the angle of attack, to operate at off-design conditions for extended periods, which results in a noticeable decline in inlet performance. To solve this problem, the local-turning osculating cones (LTOCs) method is extended from external flow to internal flow, and a three-dimensional inward-turning inlet design method under the cruising angle of attack is then proposed. In this method, the inward-turning inlet is divided into the shock-based and pressure-based segments, derived by specifying the incident 3D shock wave and the streamwise wall pressure distributions in each stream surface respectively. Numerical results demonstrate that the newly proposed method can accurately re-produce the preassigned shock waves and internal flowfield under the cruising angle of attack, thereby resulting in full mass flow capture. Compared with the inlet without considering the angle of attack, the inviscid mass-flow-capture coefficient of the inlet de-signed under the cruising angle of attack is improved by 1.94%, and the inviscid total pressure recovery coefficient at the throat section is improved by 6.56% when the compression performances of two inlets are essentially identical. Under the viscous conditions, the mass-flow-capture coefficient is augmented by 1.90%, the total pressure recovery coefficient at the throat section is enhanced by 6.69%, and the total pressure recovery coefficient at the isolator’s exit section is elevated by 7.13%.

Key words： Hypersonic; Inward-turning inlet; Cruising angle of attack; Mass-flow-capture; Total pressure recovery

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