Anew flapping-wing model of MAV(Micro Air Vehicle) with flexible structure was developed in order to explore mechanism of lift and thrust generation in flexible flapping-wing MAV.Wind tunnel test demonstrated the downstroke of the flapping-wing by utilizing laser instrument.Variation of the lift and thrust of flexible flapping-wing under conditions of different flap parameters such as flap frequency

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flow speed and so on was investigated and compared with computed results.The research provides reference for design of flapping-wing MAV.The flight tests of the Flexible Flapping-wing MAVconducted in Research Center of MAVof NUAAwere also successfully completed.