The flowfield around a pitching aerofoil, especially the phenomenon of dynamic stall, has been attracting intensive reasearch in recent decades. The perceived benefits of the research apply, for example, to helicopters, high-agility fighter aircraft, and wind turbines. In the case of the helicopter, the main rotor blade section operates in a periodic aerodynamic environment during forward flight. A modified discrete vortex method to simulate the separated flow around an aerofoil undergoing pitching motion is described. The vorticity generated in the thin layer around the body is discretized into vortices in accordance with the multipanel surface representation. By convection and diffusion the vortices are released from the body and advanced in the wake as determined by the Biot-Savart law and random-walk model, respectively. Both unsteady static and pitching cases are presented, and comparison with the test data illustrates that, without prior knowledge of the developing separation and reattachment points for the model, good agreement has been achieved.
Discrete vortex method for simulating unsteady flow around pitching aerofoils
Methode der diskreten Wirbelbelegung zur Simulation der instationären Strömung um Tragflügel mit zeitlich veränderlichem Anstellwinkel
AIAA Journal ; 35 , 3 ; 494-499
1997
6 Seiten, 10 Bilder, 15 Quellen
Article (Journal)
English
Discrete Vortex Method for Simulating Unsteady Flow Around Pitching Aerofoils
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