Wind-Tunnel Experimental Investigation on a Fix-Wing Micro Air Vehicle

摘要

Force measurement was conducted to investigate aerodynamics of the micro air vehicle with a thick fixed-wing at low Reynolds number. In the experiment, the position of vertical stabilizer and leading-edge sweepback angle of wing were variable parameters. Experimental results display that longitudinal aerodynamics of the micro air vehicle with thick wing is favorable. It is found that sweepback angle is an important parameter to static lateral stability, which has strong effects on the value of roll moment and yaw moment. Roll-moment coefficient C_l and derivative C_l~β of the micro air vehicle with 35-deg sweepback wing is greater, whereas C_n is smaller while sweepback angle is 35 deg. Smaller sweepback angle increases maximum lift coefficient and delays stalling. The results also show that the position of vertical stabilizer mainly affects directional stability. It is indicated that the vertical stabilizer set up at wing tip has the advantages of increase in lateral aerodynamics and improvement of lateral stability. The results provide an insight into thick LAR wing at low Reynolds number and supply a good reference for the design of micro air vehicles. Nevertheless, there are many problems about flow structure and interaction to be clarified, and further researches on thick wings with LAR at low Reynolds number are expected.