In current integrated aircraft/engine research, the internal and external flow coupling effect induced by crosswind has gradually become a research focus. To achieve rapid integrated simulation of high bypass ratio nacelle/fan configurations under crosswind conditions, the streamwise body force model (SBFM) is improved by introducing a radial region strategy, yielding the Radial Region Streamwise Body Force Model (RSBFM). Comparisons against URANS (Unsteady Reynolds-Averaged Navier-Stokes) results indicate that RSBFM is capable of more accurately capturing the mass flow variation and flow separation phenomena under crosswind conditions, with the overall mass flow characteristics deviating by less than 1
This paper introduces a unidirectional air turbine with three-dimensional twisted blades, designed to improve energy conversion efficiency. The blade design was based on the streamline curvature method. Computational Fluid Dynamics (CFD) simulations were used to analyze performance metrics such as pressure difference, aerodynamic torque, and efficiency across different airflow rates and rotational speeds. These simulations showed a peak efficiency of 75
To address the adverse effects of substantial incidence fluctuations on aerodynamic performance under off-design conditions, this study investigates a curved blade design strategy aimed at enhancing incidence tolerance for high through-flow (HTF) turbines. By developing an approximate loss model for curved blades, the mechanism through which geometric parameters influence aerodynamic loss is elucidated, demonstrating that positive curved blades exhibit superior robustness than negative curved blades across the entire incidence range. The optimized curved blade cascade (CBC) induces only slight loss increase over a narrow incidence range of 31
To identify the key governing factors influencing the aerodynamic performance and positive incidence operational range (PIOR, the range of positive incidence conditions over which the airfoil can maintain low aerodynamic loss) of subsonic compressor blade airfoil, this study employs an airfoil parametrization method that integrates cascade physical geometric parameters into the camber line definition to conduct a systematic analysis of key geometric parameters that affect aforementioned aerodynamic characteristics, with the aim of elucidating their underlying mechanisms. Sensitivity analysis based on Response Surface Methodology (RSM) reveals that the tangential angle at the junction between the Forward Cascade Section (FCS) and the Middle Cascade Section (MCS) of airfoil, as well as the leading edge radius, are the key parameters exerting the most significant influence on both aerodynamic loss and the PIOR of the airfoil. Further analysis integrated with numerical simulations reveals that: increasing the tangential angle at the FCS-MCS junction adjusts the load distribution between FCS and MCS, thereby controlling boundary layer development on the suction surface; increasing the leading edge radius modifies the curvature distribution near the leading edge, effectively stabilizing the suction-side boundary layer at its initial stage, and both mechanisms significantly enhance separation resistance under larger positive incidence conditions. Finally, through multi-objective optimization of the original airfoil, the total pressure loss at +6° incidence angle is reduced by 48.12
