Numerical Investigation of a Dynamic Stall on a Single Rotating Blade
نویسندگان
چکیده
Dynamic stall is a phenomenon on the retreating blade of helicopter which can lead to excessive control loads. In order understand dynamic and fill gap between investigations pitching wings full rotor blades, numerical investigation single rotating carried out. The flow phenomena thereupon including Ω-shaped vortex, interaction leading edge vortex with tip newly noticed structure originating inboard are examined; they show similarities wings, while also possessing their unique features system. edge/tip dominates post-stall stage. A swell observed have great impact load in With such high Reynolds number, Coriolis force exerted negligible compared pressure force. history/vortex slice r/R = 0.898 2D airfoil same harmonic pitch motion, current simulation shows important role played by recovery
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ژورنال
عنوان ژورنال: Aerospace
سال: 2021
ISSN: ['2226-4310']
DOI: https://doi.org/10.3390/aerospace8040090