Validation of the steady state hover formulation for accurate performance predictions

This paper shows accurate predictions for hover performance regardless of planform geometry, blade-tip Mach number, or disk loading. To prove this statement, sensitivity analyses were performed along with performance predictions for four rotor designs. Planform effects were also studied, such as the blade anhedral, showing the strong sensitivity of the rotor blade performance due to geometric features. The steady-state solution methodology with imposed Froude boundary conditions is shown to give accurate results for relatively coarse grid sizes. This approach leads to reduced computational costs as compared to time-dependent simulations. It is also recognized that, given the current accuracy of the available experimental data, the use of more advanced computational fluid dynamics methods may not be fully justified. To advance the accuracy of modern computational fluid dynamics methods, a comprehensive experimental dataset is required