Geometric sensitivity analysis of the DSI inlet

SHU Bowen; GAO Zhenghong; HUANG Jiangtao; ZHONG Shidong; ZHENG Haibo

doi:10.7638/kqdlxxb-2024.0010

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Geometric sensitivity analysis of the DSI inlet

更新时间：2026-07-27

- Geometric sensitivity analysis of the DSI inlet
- Vol. 42, Issue 9, Pages: 100-113(2024)
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 中国空气动力研究与发展中心空天技术研究所,绵阳,621000
  3. 飞行器基础布局全国重点实验室,西安,710072
  4. 中国空气动力研究与发展中心跨域飞行交叉技术重点实验室,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0010
  CLC： V231
- Published：2024
- 稿件说明：
移动端阅览
舒博文, 高正红, 黄江涛, 等. 低可探测DSI进气道几何敏感性分析[J]. 空气动力学学报, 2024, 42(9): 100−113.

SHU Bowen, GAO Zhenghong, HUANG Jiangtao, et al. Geometric sensitivity analysis of the DSI inlet[J]. 2024, 42(9): 100-113.
舒博文, 高正红, 黄江涛, 等. 低可探测DSI进气道几何敏感性分析[J]. 空气动力学学报, 2024, 42(9): 100−113. DOI： 10.7638/kqdlxxb-2024.0010

SHU Bowen, GAO Zhenghong, HUANG Jiangtao, et al. Geometric sensitivity analysis of the DSI inlet[J]. 2024, 42(9): 100-113. DOI： 10.7638/kqdlxxb-2024.0010.

摘要

低可探测DSI进气道（蚌式进气道）设计受多个几何参数的影响，单几何参数分析难以全面反映外形对进气道性能的影响。本文采用非嵌入式多项式混沌方法对某低可探测DSI进气道开展研究，分析亚声速大攻角、最大飞行速度时，进气道性能对喉道面积、喉道位置、鼓包马赫数、鼓包前移量、唇罩前伸量、唇口前缘半径以及进气道收缩量的敏感程度，并开展了选型设计。结果表明，进气道性能对唇罩前伸量最敏感，鼓包马赫数和收缩量对亚声速大攻角下的进气道性能也有所贡献，并存在最佳的唇罩前伸量与进气道收缩量。选型设计后，进气道在亚声速大攻角时总压恢复系数提升4.6%，稳态总压畸变指数下降10.9%；在最大飞行速度时总压恢复系数提升3.1%，稳态总压畸变指数降低35.5%。合理地选择几何参数，减弱或消除进气道唇口处以及激波后的分离能够有效提升进气道性能。

Abstract

The design of a low detectable supersonic inlet (DSI) involves the influence of multiple geometric parameters

making it challenging to fully reflect their impact on the inlet performance through a single parameter analysis alone. To address this issue

a non-intrusive polynomial chaos method was employed to study the low detectable supersonic inlet

by performing a sensitivity analysis of the inlet performance to various geometric parameters such as throat area

throat location

bump Mach number

bump forward amount

lip length

lip leading-edge radius

and inlet contraction amount under conditions of subsonic flow with high attacking angles as well as flow at the highest flight speed. Based on these findings

a selection design of inlets was conducted. The results reveal that the lip length is the most sensitive parameter

while both the bump Mach number and the bump contraction amount also contribute to the inlet performance improvement at low-speed flow with high attacking angles. After the selection design process

the total pressure recovery coefficient and the steady-state distortion index are increased and decreased by 3.1% and 35.5%

respectively

under the condition of the highest flight speed; the corresponding two values are 4.6% and 10.9% under the condition of low-speed flight with high attacking angles. These outcomes highlight the overall inlet performance can be effectively enhanced by appropriate selection of geometric parameters as well as attenuation or elimination of flow separation around the inlet lip or after the shock waves.

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Keywords

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