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A comprehensive rotorcraft simulation code is used to predict the rotor maximum thrust limit (due to stall limits) in hover and the thrust and power characteristics when the collective control angle is further increased. The aerodynamic modeling factors that may significantly affect the results are: steady vs. unsteady aerodynamics, steady vs. dynamic stall, blade tip losses, curvature flow, yaw angle, inflow model, and blade-vortex interaction.

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Comprehensive Code Modeling Impact on Maximum Thrust, and Beyond, of an Isolated Rotor in Hover: Application of a Free-Wake Method

  • 会议论文

  • 发表日期：

    2026年

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  • Berend G. van der Wall

摘要

A comprehensive rotorcraft simulation code is used to predict the rotor maximum thrust limit (due to stall limits) in hover and the thrust and power characteristics when the collective control angle is further increased. The aerodynamic modeling factors that may significantly affect the results are: steady vs. unsteady aerodynamics, steady vs. dynamic stall, blade tip losses, curvature flow, yaw angle, inflow model, and blade-vortex interaction.