Flexible wing and rotor blade designs operating at low Mach number ($M\le 0.3$) environments may undergo or need to avoid stall flutter and, therefore, accurately predict dynamic stall airloads. At the preliminary stage, aeroelastic calculations routines place a limit on computational expenses and demand low-order models. However, the semi-empirical dynamic stall models used for such purposes still present some flaws for low freestream speeds, especially under stall onset and light stall conditions. Given that, the present paper proposes improvements for the Beddoes–Leishman model. Building upon past modifications for the low-speed dynamic stall, several modeling strategies for the onset of stall, reattachment, and vortex-shedding processes are introduced. These enhancements are extensively validated with previously available experimental data for the symmetric NACA 0012 and cambered AMES-01 airfoils, showing superior results over the base model for virtually all conditions tested, albeit requiring up to 40% longer computational time.

灵活的机翼和转子叶片设计以低马赫数运行（$米\le 0.3$) 环境可能经历或需要避免失速颤振，因此，准确预测动态失速空载。在初步阶段，气动弹性计算例程对计算费用和需求低阶模型进行了限制。然而，用于此类目的的半经验动态失速模型对于低自由流速度仍然存在一些缺陷，尤其是在失速开始和轻微失速条件下。鉴于此，本文提出了对 Beddoes-Leishman 模型的改进。在过去对低速动态失速的修改的基础上，介绍了几种失速开始、重新附着和涡旋脱落过程的建模策略。这些增强功能已通过先前可用的对称 NACA 0012 和弧形 AMES-01 翼型的实验数据得到广泛验证，