Abstract
The scope of this Paper is to investigate the integration effects of turboprop engines on a high-lift wing with an internally blown plain flap system with Reynolds-averaged Navier–Stokes computations. It is shown that the resulting nacelle vortices can significantly reduce the high-lift performance at zero thrust conditions. To limit the negative impact, an inboard nacelle strake was designed with the aim of maximizing the lift coefficient of the landing configuration at zero thrust. To reach this goal, a sensitivity study on basic geometric strake parameters was carried out. The best nacelle strake is able to improve the maximum lift coefficient by and the maximum angle of attack by 3 deg. The study also reveals the further potential of improvement due to an additional outboard strake. First simulations with outboard strake lead to a further improvement of and 4 deg in the maximum angle of attack. It is also shown that the installation of an inboard strake does not negatively impact the high-lift performance at a moderate thrust level.
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