Aerodynamic efficiency analysis of the ridge integrated submerged inlet

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering Pub Date : 2024-01-16 DOI:10.1177/09544100241226991

Eiman B Saheby, Xing Shen, Saeed Jowkar

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Abstract

In this study, a new ridge surface is proposed and its impact on the aerodynamic efficiency of a generic top-mounted submerged inlet is investigated at Mach 0.3 to 0.5. The concept is developed to investigate the possibility of vortex breakdown manipulation by the ridge surface to control the chaotic flow pattern after the breakdown, measuring the overall drag increment and total pressure recovery due to the ridge integration. For this purpose, a conceptual submerged inlet is designed with a semi-elliptic entrance for integration with a generic fuselage and ridge surfaces; then different study cases are modeled based on this configuration for numerical simulations by Ansys Fluent. Key factors such as the quality of the captured streamtube, vortex patterns on the fuselage, induced lift, and vortex breakdown patterns are investigated and compared by second order accuracy. Results indicate that the modified ridge surface improves the overall efficiency of the fuselage-inlet configuration both in the terms of lift over drag and pressure recovery.

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山脊一体化沉没式进气口的气动效率分析

在这项研究中，提出了一种新的脊面，并研究了它在 0.3 至 0.5 马赫时对一般顶部安装的沉没式进气口的气动效率的影响。提出这一概念的目的是为了研究脊面操纵涡流击穿的可能性，以控制击穿后的混乱流型，测量脊面整合带来的整体阻力增量和总压力恢复。为此，设计了一个具有半椭圆形入口的概念性浸没式进气口，用于与通用机身和脊面进行集成；然后根据该配置建立了不同的研究案例模型，并通过 Ansys Fluent 进行了数值模拟。研究并比较了捕获流管的质量、机身上的涡流模式、诱导升力和涡流击穿模式等关键因素的二阶精度。结果表明，改进后的脊面在升力超过阻力和压力恢复方面提高了机身进气口配置的整体效率。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

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