Output details

Aerodynamic Stall Suppression on Aerofoil Sections Using Passive Air-Jet Vortex Generators

This paper presents work on development of the passive air jet vortex generator, comparing experimental measurements with detailed computational simulations to identify the important physical mechanisms in suppression of turbulent boundary layer separation on two aerofoil blade models - a full scale helicopter section and a wind turbine blade. The technology is demonstrated, for the first time on an aerofoil to deliver up to 20% increase maximum lift coefficient, delaying stall by 3 degrees angle-of-attack. The method is an improvement over vane vortex generators, delivering equivalent performance improvements without the detriment of increased pressure drag.