Computational Study of Aerodynamic Characteristics of Elliptic Airfoils for Rotor/Wing UAV Applications
The aerodynamic characteristics of several elliptic airfoils with thickness ratios from 10％ to 18％ were numerically investigated by solving the Reynolds Averaged Navier-Stokes (RANS) equations and the shear stress transport (SST) k-ω two-equation turbulence model was chosen to evaluate the effect of turbulence. The methodology used to conduct the computational analysis was validated by comparing the CFD results with wind tunnel test results. Investigations were performed for Mach number of 0.4 and Reynolds number of 1.3×106 at free stream. The results shown that, at attack angles less than stall angle, better lift, drag and pitching moment performance were observed for lower thickness ratios. However, the stall angle of attack and maximum lift coefficient increased as the thickness ratio increased. The results of this investigation could be used in the design and development of future rotor/wing UAV.
aerodynamic characteristics elliptic airfoil rotor/wing SST k-ω two-equation turbulence model
Deng Yangping Gao Zhenghong Zhan Hao
National Key Laboratory of Aerodynamic Design and Research, Northwester Polytechnical University, Xian 710072 China
国际会议
南京
英文
1-5
2009-10-14（万方平台首次上网日期，不代表论文的发表时间）