Aerodynamic Improvement of Flap Performance Using Delta-shaped Vortex Generator

摘要：

Low-speed wind tunnel tests were performed to investigate aerodynamic effects of a delta-shaped vortex generator that was installed on the upper surface of the trailing edge flap. The vortex generator was applied for controlling the flow over the trailing edge flap. The test results were showed that the vortex generator increases the lift coefficient and the lift-to-drag ratio when the trailing edge flap deflects to 30deg. The leading edge separation vortices formed by the vortex generator acted to suppress the flow separation from the flap hinge line. The height of the vortex generator is geometrically decided from the flap deflection angles. When the flap deflection angle was zero, no drag penalty was obtained because the height of the vortex generator was zero.

关键词： Trailing edge flap Vortex generator Flow separation Flow control

作者: Dongyoun Kwak Zhong Lei Masayoshi Noguchi

作者单位: Aviation Program Group, Japan Aerospace Exploration Agency, Mitaka, Tokyo, 181-0015, Japan Department of Mechanical Systems Engineering, Tokyo University of Science, Suwa, Nagano, 391-0292, J

会议类型: 国际会议

会议名称: 2011年亚太航空航天技术学术会议(APISAT 2011)

会议地点: 澳大利亚

会议语种:英文

页码: 1-7

在线出版日期: 2011-02-28（万方平台首次上网日期，不代表论文的发表时间）