摘要
Based on the results of force measurement experiment in a low speed wind tunnel, the effect of asymmetrical leading-edge sweep angle on aerodynamic load was investigated with the common-swift’s wing model. The wing model was divided into three segments, i.e., arm wing, hand wing<SUB>in</SUB> and hand wing<SUB>out</SUB>, and the roll moment produced by the variation of asymmetrical change of wing segment’s leading-edge sweep angle was analyzed.
基金
Supported by the National Natural Science Foundation of China (Grant No. 10425207)
