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Kryukov A.V.   Kozlov V.V.   Zverkov I.D.  

Flow separation elimination on subsonic plane wing via applying of complex undulations.

Reporter: Kryukov A.V.

Nowadays, micro air vehicles (MAV) find new military and civil applications. Miniaturization of the electronic equipment promotes the creation of progressively smaller unmanned aircraft. At the moment, many researchers pay much attention to MAVs with an overall mass below 0.5 kg and a chord-based Reynolds number between 104 and 105. In spite of certain success, the wide application of MAVs is limited by their rather modest aerodynamic performances. Important MAV parameters, such as the critical angle of attack and lift-to-drag ratio, are mainly deteriorated by changes in the boundary-layer flow character at low Reynolds numbers. Wing surface modification is one of the major resources of separation control and aerodynamic performance improvement. The one of most aspects is to consider the effect of spanwise-periodic modifications to the wing surface on the laminar boundary-layer separation. As in our previous work was demonstrated [ ], the wavy wing stall angle of attack is 1.5 times higher than classical wing one and aerodynamic performance hysteresis was not observed.
Ability of total separation elimination via complex undulations considered at presented work. The data obtained on wavy wing with mounting secondary undulations in the groove of main undulations by oil-film flow visualization picture. At result received that separation of flow is disappear with secondary undulations installing at special area near local separation bubble. Moreover the effect existence doesn't depend of wing profile. Only three dimensional pressure gradient distribution important for effect appearing.

 


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