Summary The laminar flow around a NACA 4402 airfoil is investigated at a Reynolds number of Re = 6000 using the RANS solver FLOWer. Significant flow separation occurs over almost the whole regime of angles of attack for steady onset flow conditions. Therefore, the calculated propulsive efficiencies of pure plunge motions are rather poor. This leads to the need of a combined plunge and pitch motion, which is investigated subsequently. For combined motions, cases with high propulsive efficiencies are found over a wide range of produced thrust.
Aerodynamic Analysis of Flapping Airfoil Propulsion at Low Reynolds Numbers
2005-01-01
15 pages
Article/Chapter (Book)
Electronic Resource
English
Aerodynamic Analysis of Flapping Airfoil Propulsion at Low Reynolds Numbers
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