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A main wing structure comprises at least a leading edge structure and a wing central structure coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface, a lower wing surface, a leading edge and a trailing edge. The upper wing surface i

A main wing structure comprises at least a leading edge structure and a wing central structure coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface, a lower wing surface, a leading edge and a trailing edge. The upper wing surface includes: a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located at 38% of a wing chord length; a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point 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 by a distance 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 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. Coupled portions between the leading edge structure and the wing central structure 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.

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1. A main wing structure comprising at least a leading edge structure and a wing central structure coupled to each other,wherein said main wing structure has a laminar-flow airfoil comprising an upper wing surface, a lower wing surface, a leading edge and a trailing edge,said upper wing surface incl

1. A main wing structure comprising at least a leading edge structure and a wing central structure coupled to each other,wherein said main wing structure has a laminar-flow airfoil comprising an upper wing surface, a lower wing surface, a leading edge and a trailing edge,said upper wing surface including:a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located in a range of 30% to 50% of a wing chord length;a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point 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 by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.12; anda rear profile portion 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, andwherein coupled portions between said leading edge structure and said wing central structure are arranged at positions corresponding to approximately 20% of the wing chord length. 2. The main wing structure according to claim 1, wherein the largest-thickness point is approximately 38% of the wing chord length. 3. The main wing structure according to claim 1, and further including a transition point at which the laminar-flow boundary layer region changes to a turbulent-flow boundary layer region. 4. The main wing structure according to claim 3, wherein the transition point is approximately 42% of the wing chord length. 5. The main wing structure according to claim 1, and further including a largest-thickness position disposed on the lower wing surface for forming a laminar-flow boundary layer region. 6. The main wing structure according to claim 5, wherein the largest-thickness position disposed on the lower wing surface is approximately 49% of the wing chord length. 7. The main wing structure according to claim 5, and further including a transition point disposed on the lower wing surface at which the laminar-flow boundary layer region changes to a turbulent-flow boundary layer regions. 8. The main wing structure according to claim 7, wherein the transition point disposed on the lower wing surface is approximately 63% of the wing chord length. 9. A main wing structure comprising at least a leading edge structure and a wing central structure coupled to each other,wherein said main wing structure has a laminar-flow airfoil comprising an upper wing surface, a lower wing surface, a leading edge and a trailing edge,said upper wing surface including:a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located in a range of 30% to 50% of a wing chord length;a central profile portion which is rectilinear a positive curvature radius, and which is provided to extend from the largest-thickness point 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 by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.12; anda rear profile portion 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, andwherein coupled portions between said leading edge structure and said wing central structure are arranged at positions corresponding to approximately 20% of the wing chord length. 10. The main wing structure according to claim 9, wherein the largest-thickness point is approxima tely 38% of the wing chord length. 11. The main wing structure according to claim 9, and further including a transition point at which the laminar-flow boundary layer region changes to a turbulent-flow boundary layer region. 12. The main wing structure according to claim 11, wherein the transition point is approximately 42% of the wing chord length. 13. The main wing structure according to claim 9, and further including a largest-thickness position disposed on the lower wing surface for forming a laminar-flow boundary layer region. 14. The main wing structure according to claim 13, wherein the largest-thickness position disposed on the lower wing surface is approximately 49% of the wing chord length. 15. The main wing structure according to claim 13, and further including a transition point disposed on the lower wing surface at which the laminar-flow boundary layer region changes to a turbulent-flow boundary layer regions. 16. The main wing structure according to claim 15, wherein the transition point disposed on the lower wing surface is approximately 63% of the wing chord length. 17. A main wing structure comprising at least a leading edge structure and a wing central structure coupled to each other,wherein said main wing structure has a laminar-flow airfoil comprising an upper wing surface, a lower wing surface, a leading edge and a trailing edge,said upper wing surface including:a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located in a range of 30% to 50% of a wing chord length;a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point 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 by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than a predetermined number; anda rear profile portion which has a negative curvature radius or is rectilinear, 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, andwherein coupled portions between said leading edge structure and said wing central structure are arranged at positions corresponding to approximately 20% of the wing chord length. 18. The main wing structure according to claim 17, wherein the largest-thickness point is equal to or smaller than 0.12. 19. The main wing structure according to claim 17, wherein the central profile portion extends to the vicinity of a position corresponding to approximately 90% of the wing chord length. 20. The main wing structure according to claim 17, wherein the rear profile portion extends to a position corresponding to approximately 95% of the wing chord length.