An aircraft structure comprising: an edge panel comprising a first edge panel portion and a tapered second edge panel portion, wherein the first edge panel portion is a constant first thickness, wherein the tapered second edge panel portion comprises a first end proximal to the first edge panel portion and a second end distal to the first edge panel portion, and wherein the tapered second edge panel portion decreases in thickness from the first end to the second end; and a skin comprising: a first portion; a second portion; and a first bend disposed between the first portion and the second portion, wherein the first portion and the second portion are of a substantially constant second thickness, wherein at least a part of the second portion is disposed below at least a part of the tapered second edge panel portion, and wherein the second thickness is greater than the first thickness; wherein the skin further comprises a third portion and a second bend disposed between the second portion and the third portion, wherein the first portion is substantially parallel to the third portion, and wherein the third portion is disposed below the first edge panel portion; wherein the aircraft structure further includes a fastener coupling together the third portion and the first edge panel portion (312A; wherein the tapered second edge panel portion is a multi-ply composite, and wherein the tapered second edge panel portion decreases in thickness by decreasing an amount of plies, wherein a ply drop offset proximate to the first end is greater than a ply drop offset proximate to the second end, and wherein the second bend is disposed proximate to the first end. an edge panel comprising a first edge panel portion and a tapered second edge panel portion, wherein the first edge panel portion is a constant first thickness, wherein the tapered second edge panel portion comprises a first end proximal to the first edge panel portion and a second end distal to the first edge panel portion, and wherein the tapered second edge panel portion decreases in thickness from the first end to the second end; and a skin comprising: a first portion; a second portion; and a first bend disposed between the first portion and the second portion, wherein the first portion and the second portion are of a substantially constant second thickness, wherein at least a part of the second portion is disposed below at least a part of the tapered second edge panel portion, and wherein the second thickness is greater than the first thickness; wherein the skin further comprises a third portion and a second bend disposed between the second portion and the third portion, wherein the first portion is substantially parallel to the third portion, and wherein the third portion is disposed below the first edge panel portion; a first portion; a second portion; and a first bend disposed between the first portion and the second portion, wherein the first portion and the second portion are of a substantially constant second thickness, wherein at least a part of the second portion is disposed below at least a part of the tapered second edge panel portion, and wherein the second thickness is greater than the first thickness; wherein the skin further comprises a third portion and a second bend disposed between the second portion and the third portion, wherein the first portion is substantially parallel to the third portion, and wherein the third portion is disposed below the first edge panel portion; wherein the aircraft structure further includes a fastener coupling together the third portion and the first edge panel portion (312A; wherein the tapered second edge panel portion is a multi-ply composite, and wherein the tapered second edge panel portion decreases in thickness by decreasing an amount of plies, wherein a ply drop offset proximate to the first end is greater than a ply drop offset proximate to the second end, and wherein the second bend is disposed proximate to the first end.