Experimental Study of Optimal Staggered Configuration Aerodynamics of Flat-plate Cascade-wing Micro Aerial Vehicle

• Main Authors: Hung Kao, 高鴻
• Other Authors: Fei-Bin Hsiao
• Format: Others
• Language: zh-TW
• Published: 2005
• Online Access: http://ndltd.ncl.edu.tw/handle/65485171769617880537

碩士 === 國立成功大學 === 航空太空工程學系專班 === 93 === 　　This thesis is intended to investigate the aerodynamic characteristics of the flat-plate cascade-wing Micro Aerial Vehicle (MAV) at low Reynolds number by wind-tunnel testing and to determine the optimal staggered configuration of the wings for the MAV. There were 16 cascade-wing models of flat-plate airfoil with different overlap ratios and gap ratios along with a monoplane of AR=1.6 tested at the Reynolds number of 8.8×104 for comparison. The lift and drag forces were measured and normalized based on the total area of the cascade wings. In order to understand the flow structure behavior around the cascade wings, the flow visualization was performed as well in a smoke tunnel. Results indicate that the stall angles of attack (AOA) for all the cascade-wing models tested were all exceeding 20 degrees and the corresponding maximum lift coefficients were larger than that of the monoplane model with the same wing area. The values of lift coefficients vary mildly near the stall angles. According to the lift-to-drag ratio calculation, the performance of cascade-wing models is usually inferior to the monoplane, but it may be very close when the arrangements of cascade wings are adequate. It was observed in flow visualization that the flow can be attached to the surfaces of lower wing when the flow had separated from the upper wing at high AOA; hence the cascade wing can maintain its lift force at even higher AOA. It is induced that the overlap ratio has much influence on the lift at high AOA. The optimum values of configuration parameters are overlap ratio O=0 and gap ratio G=0.48.