本文依据翼身融合式飞行器的设计理念设计一种飞翼式水下滑翔机，及其主要设计参数。通过计算发现该飞翼式水下滑翔机较传统水下滑翔机拥有更大的升阻比，可达到15以上。流场分布结果显示飞翼式水下滑翔机在特定速度0.1 m/s、0.3 m/s和0.5 m/s下，机翼周围并未出现明显的流动分离，且机翼表面压力较大程度取决于攻角的大小。对比了不同雷诺数下的机翼表面涡脱落情况，发现随着攻角增大涡的脱落急剧增多，且翼梢小翼尾部涡脱落最为严重，极大影响滑翔机的水动力特性。
This paper designs a flying wing underwater glider based on the design concept of wing-body fusion aircraft, and its main design parameters. Through calculation , it is found that the flying wing underwater glider has a higher lift-to-drag ratio than the traditional underwater glider, which can reach more than 15. The flow field distribution results show that there is no significant flow separation around the wing of a flying wing underwater glider at specific speeds of 0.1 m/s, 0.3 m/s, and 0.5 m/s. The surface pressure of the wing depends greatly on the Angle of attack. By comparing the vortex shedding on the wing surface under different o Reynolds numbers, it is found that the vortex shedding increases sharply with the increase of the Angle of attack, and a large number of vortices appear at the tail of the wingtip small wing, which greatly affects the motion state of the glider.
2024,46(6): 90-97 收稿日期：2023-03-30
DOI：10.3404/j.issn.1672-7649.2024.06.016
分类号：U674.941
基金项目：江苏省高层次创新创业人才引进计划资助项目（JSSCBS20211001）
作者简介：熊仲营(1985-),男,博士,讲师,研究方向为流动控制、仿生设计、多目标优化设计等
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