Zejun CAI, Xiaogang ZHENG, Waner HU, Zhancang HU, Chengxiang ZHU, Yancheng YOU

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST 2024-0043

The hypersonic inlet plays a pivotal role in achieving hypersonic flight in air-breathing aircraft. Its primary function is to supply compressed air to meet the engine’s demands across the entire flight envelope of the aircraft, encompassing acceleration, deceleration, and cruise phases. Consequently, inlet design must cater to the requirements of this wide speed range. Scholars have pursued research on various hypersonic inlet designs to attain this objective. In recent years, the inward-turning inlet has gained significant attention due to its advantages in compression, flow capture, and frontal area reduction. Prominent examples like the SR-72, HAWC, and Boeing hypersonic aircraft have all adopted the inward-turning inlet configuration. However, conventional methods often necessitate iterative optimization to account for a wide domain of performance requirements, lacking a reverse design method based on comprehensive aerodynamic demands. In this paper, a double design point (DDP) inward-turning inlet design method is proposed which considers the needs of two distinct design point operating characteristics, and enhanced design flexibility through the osculating design approach.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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