Abstract: The streamlining section of non-lift column shaped component normally observed in some subsonic aircrafts is investigated by numerical method. A new series of variable elliptic section is advanced, which is defined by the conic shape parameter Rho and the maximum thickness position. The comparison of drag, lift and structural property of ellipse section, airfoil section and the new elliptic sections is performed with fineness ratio from 1.5 to 8. The CFD analysis reveals that airfoil section has the minimal drag when fineness ratio is larger than 3, but further decrease of fineness ratio could cause special phenomena such as negative lift slope and drag increase. The elliptic section has the highest drag, while the proposed new section has the intermediate value, which could be further reduced when the shape is closer to an airfoil. It is notable that the elliptic sections with variable parameters could maintain reasonable drag and lift characteristics even for the case when the fineness ratio drops to 2. The airfoil has the highest lift curve slope when fineness ratio is bigger than 3, but is prone to flow separation and rapid change of lift curve slope when the fineness ratio is lowered. On the contrary, the ellipse behaves steadily at low fineness ratio, while the new sections have smaller drag at low fineness ratios. The structure property is evaluated by two parameters: the average section thickness and the cross-section area. With no surprise the ellipse is the best one in structure with its rounded shape and the airfoil behaves the worst, and the new elliptic section lies between the two. By comparing the overall performance, the elliptic section with Rho 0.414/0.35 configuration seems to combine the advantages of both the airfoil and the ellipse, which enables it better aerodynamic fairing section for its enhanced overall aerodynamic-structural property.