| 摘要 |
A main wing structure comprises at least a leading edge structure (11) and a wing central structure (12) coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface (Su), a lower wing surface (Sl), a leading edge (El) and a trailing edge (Et). The upper wing surface includes: a front profile portion (Cf) which has a positive curvature radius, and which is provided to extend from the leading edge (El) to a largest-thickness point (Ta) located at 38% of a wing chord length; a central profile portion (Cc) which has a positive curvature radius, and which is provided to extend from the largest-thickness point (Tu) to the vicinity of a position corresponding to approximately 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point ( DELTA t) by a distance (L) in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.12; and a rear profile portion (Cr) which has a negative curvature radius, and which is provided to extend from the vicinity of a position corresponding to approximately 95% of the wing chord length to the trailing edge (Et). Coupled portions between the leading edge structure (11) and the wing central structure (12) are arranged at positions corresponding to approximately 20% of the wing chord length. Thus, it is possible to minimize an increase in drag due to a gap and a step between the coupled portions between the leading edge structure and the wing central structure. <IMAGE>
|
