A curved wing tip connected to a wing for an airplane, the wing having a wing leading edge and a wing trailing edge, wherein the wing leading edge and the wing trailing edge are swept rearward, the curved wing tip comprising: a leading edge curved to maintain attached air flow and defining a first elliptic line from the wing leading edge to a leading end point; a trailing edge curved to maintain elliptic loading over the curved wing tip defining a second elliptic line from the wing trailing edge to a trailing end point; and an end segment connecting the leading end point and the trailing end point swept at an end segment angle to maintain a trailing vortex position close to the trailing end point 432, wherein the curved wing tip is defined by a set of sizing parameters to constrain an overall proportion of the curved wing tip, including: a wing tip height h measuring the distance in a direction orthogonal to an x-axis from a transition point between the wing and the curved wing tip to the leading end point, wherein the x-axis runs along the longitudinal axis of the airplane from nose to the tail, and wherein the transition point corresponds to the origin of the trailing edge of the curved wing tip at the wing trailing edge; a wing tip length g measuring the distance parallel to the x-axis from the transition point to the leading end point; an initial chord length C 1 measuring a chord length parallel to the x-axis at the transition point; an end chord length C 2 measuring a chord length from the leading edge to the trailing edge parallel to the x-axis at the trailing end point; wherein g/ C 1 is in the range of about 0.50 to about 0.80, h/ C 1 is in the range of about 0.60 to about 1.00, and C 2 /C 1 is in the range of about 0.60 to about 0.70, wherein the leading edge forms the first elliptic line starting generally tangential with the wing leading edge and approaching a freestream direction U at the leading end point, and wherein the trailing edge forms the second elliptic line starting generally tangential from the wing trailing edge and approaching the freestream direction U at the trailing end point, wherein the end segment is swept having the end segment angle equal to or close to a wing trailing edge sweep angle, and wherein the end segment has a length CE in the range of 0.15 < CE/h < 0.20. a trailing edge curved to maintain elliptic loading over the curved wing tip defining a second elliptic line from the wing trailing edge to a trailing end point; and an end segment connecting the leading end point and the trailing end point swept at an end segment angle to maintain a trailing vortex position close to the trailing end point 432, wherein the curved wing tip is defined by a set of sizing parameters to constrain an overall proportion of the curved wing tip, including: a wing tip height h measuring the distance in a direction orthogonal to an x-axis from a transition point between the wing and the curved wing tip to the leading end point, wherein the x-axis runs along the longitudinal axis of the airplane from nose to the tail, and wherein the transition point corresponds to the origin of the trailing edge of the curved wing tip at the wing trailing edge; a wing tip length g measuring the distance parallel to the x-axis from the transition point to the leading end point; an initial chord length C 1 measuring a chord length parallel to the x-axis at the transition point; an end chord length C 2 measuring a chord length from the leading edge to the trailing edge parallel to the x-axis at the trailing end point; a wing tip height h measuring the distance in a direction orthogonal to an x-axis from a transition point between the wing and the curved wing tip to the leading end point, wherein the x-axis runs along the longitudinal axis of the airplane from nose to the tail, and wherein the transition point corresponds to the origin of the trailing edge of the curved wing tip at the wing trailing edge; a wing tip length g measuring the distance parallel to the x-axis from the transition point to the leading end point; an initial chord length C 1 measuring a chord length parallel to the x-axis at the transition point; an end chord length C 2 measuring a chord length from the leading edge to the trailing edge parallel to the x-axis at the trailing end point; wherein g/ C 1 is in the range of about 0.50 to about 0.80, h/ C 1 is in the range of about 0.60 to about 1.00, and C 2 /C 1 is in the range of about 0.60 to about 0.70, wherein the leading edge forms the first elliptic line starting generally tangential with the wing leading edge and approaching a freestream direction U at the leading end point, and wherein the trailing edge forms the second elliptic line starting generally tangential from the wing trailing edge and approaching the freestream direction U at the trailing end point, wherein the end segment is swept having the end segment angle equal to or close to a wing trailing edge sweep angle, and wherein the end segment has a length CE in the range of 0.15 < CE/h < 0.20.