Abstract
Computational analysis of helicopter main rotor blades in ground effect
Highlights
FLOW field around helicopter blades is highly complex [1,2,3,4,5,6]
Many flow phenomena are present [5], because of the unique characteristics of helicopters, extensive experimental and numerical research is constantly being conducted for the purpose of improvement of their aerodynamic performances
Experimental data is available only for z/d = 0.83, all numerical models clearly capture the increase in aerodynamic performances in ground vicinity, i.e. for the same thrust less power is required
Summary
FLOW field around helicopter blades is highly complex [1,2,3,4,5,6]. many flow phenomena are present (e.g. unsteadiness, tip vortex formation, 3D dynamic stall, bladevortex interaction, shock/boundary-layer interaction etc.) [5], because of the unique characteristics of helicopters, extensive experimental and numerical research is constantly being conducted for the purpose of improvement of their aerodynamic performances. There exist several models with different complexity, that can be used for simulation of axis-symmetric flow field in hover and vertical flight. Data, obtained in hover and forward flight over a nominal range of advance ratios from 0.15 to 0.425, were used for validation of the numerical models.
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