科研之友
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摘要
An experimental and numerical study was performed on a Clark Y aerofoil with a 10% chord leading edge Kruger flap to examine its aerodynamic performance at Reynolds numbers of 0.6 x 10(6), 1 x 10(6), and 1.6 x 10(6), to help to identify the forces and moments acting on a basic configuration. A detailed comparison of the numerical and experimental data is presented in this paper. The leading edge flap was effective at high angles of attack with an increase in C-L of up to 18% over a conventional no flap configuration and delayed separation by up to 3 degrees. The moments around the Kruger flap rotation point were calculated from the numerical analysis as an initial stage in the design of a UAV passive flap system and they are also presented in the paper.
- 出版日期2012-7
