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Flow visualization of the wing model equipped with load control fluidic devices

Krzysiak A.

Journal of KONES

2015

Vol. 22, No. 3

117--124

In the extraordinary off-design flight conditions, such as accelerated manoeuvres or sudden gusts, wing-bending moments may grow rapidly. This may lead to damage of the wing structure. To alleviate the excessive aerodynamic loads in off-design conditions the wing-load-control systems basing on blowing devices were developed. Proposed in these work fluidic devices could be an alternative to the conventional mechanical solutions, such as symmetrical deflections of ailerons or deflection of spoilers. As a result of the CFD studies, among many considered concepts, three solutions were chosen as the most promising. Two of them, namely Fluidic Spoiler and Dual Trailing Edge Nozzles, were tested in IoA low speed wind tunnel. Fluidic Spoiler consisted of the matrix of mini nozzles located on an upper wing surface in its tip part. Air jets blown from the nozzles were influencing the main flow around the wing, leading to flow separation and as a result, to alleviation of wing bending moment. Dual Trailing Edge Nozzles system consisted of the specially shaped nozzles, located at a wing trailing edge. The system utilises the Coanda effect to change a flow circulation around the wing, leading to spanwise redistribution of aerodynamic loads. The paper presents results of the flow visualization tests carried out on the half wing model equipped with load control fluidic devices. Flow visualization was performed using a fluorescent threads illuminated with ultraviolet light. The main objective of the research was to determine the flow separation areas and its character, associated with additional air blowing on the wing surface. The experimental tests were performed in low speed wind tunnel T-3 (5-meter diameter test section) in the Institute of Aviation. For these tests the model of semi-span wing (2.4 m span), situated vertically on the endplate in wind tunnel test section was used. Wind tunnel test were performed at Mach number M = 0.1. The study was carried out in the framework of the European project STARLET.