Improvement of aerodynamic performance of a micro-air-vehicle wing

Methods of improving the wing aerodynamic performance with the help of various kinds of vortex generators were proposed. With the help of the oil-film visualization, it was shown that the wavy low aspect-ratio wing has a higher critical angle of attack and no hysteresis of aerodynamic performance when varying the angle of attack in comparison with that of the classical wing. The aerodynamic performance was measured on six-component aerodynamic weights. The wing model was fastened with the help of suspension threads. The model edges on span were rounded by the radius amounting to half of the local profile height. The wingfoil was developed for the air vehicles of the flying-wing type. At the angle of attack of 5°, the attached flow for both classical and wavy wings were observed. The oil-film visualization shows the presence of the reverse flow in the form of two vortices with the focuses located at the wing-span edges.