关键词: 边界层, 控制, 机翼, 分离流, 风洞试验

Abstract: It is well known that there is always a separation zone in the outer panel of a strake wing at large angles of attack, which leads to lower aerodynamic efficiency. In order to improve aerodynamic characteristics of the strake wing, moving surface which is part of a rotating cone was set close to the leading edge of the out wing. Visualization tests with oil flow and smoke wire and force measurement results have shown that the separation zone could be suppressed to a large extent. The maximum lift coefficient could be raised by 30%. It has been shown that moving surface is an excellent technique to control separated flow over the strake wing.

Key words: boundary layer control, wings　separated flow, wind tunnel tests