A composite panel, comprising: a base segment, a top segment, and a composite panel segment which is a is a middle segment positioned between the base segment and the top segment, the middle segment comprising a plurality of carbon fiber plies arranged along a length and a width of the middle segment, wherein the length of the middle segment comprises a longitudinal axis; the plurality of carbon fiber plies are layered into a carbon fiber stack that provides at least a portion of a thickness of the middle segment; the carbon fiber stack comprises at least 8 carbon fiber plies; each carbon fiber ply of the carbon fiber stack comprises a stiffness, wherein the stiffness of each carbon fiber ply is determined by an orientation of carbon fibers within each carbon fiber ply relative to the longitudinal axis; the plurality of carbon fiber plies of the carbon fiber stack comprises a plurality of different orientations relative to the longitudinal axis, and thus the plurality of carbon fiber plies of the carbon fiber stack comprises a plurality of different stiffnesses; and the different orientations of the plurality of carbon fiber plies of the carbon fiber stack are self-symmetric or mostly self-symmetric through the thickness of the middle segment about a midpoint (400, 500, 600) of the carbon fiber stack, where the midpoint (400, 500, 600) is parallel to the longitudinal axis wherein the midpoint of the composite panel segment is the midpoint relative to the number of carbon fiber plies that make up the carbon fiber stack, wherein the term self-symmetric indicates that the plurality of carbon fiber plies that form the composite panel segment are mirror symmetric about the midpoint of the composite panel segment, and wherein, when mostly self-symmetric, the different orientations vary from being self-symmetric in no more than two carbon fiber plies wherein the longitudinal axis is oriented at 0°; wherein the different orientations of the plurality of carbon fiber plies include 0°, 45°, 90°, and -45° relative to the longitudinal axis of the middle segment, the middle segment has an axial modulus of elasticity of from about 78.6 GPa to about 92.4 GPa [11.4 megapounds per square inch (msi) to about 13.4 msi] and a Poisson's ratio of from about 0.38 to about 0.50; and from 46% to 58% of the plurality of carbon fiber plies are oriented at 0°. a base segment, a top segment, and a composite panel segment which is a is a middle segment positioned between the base segment and the top segment, the middle segment comprising a plurality of carbon fiber plies arranged along a length and a width of the middle segment, wherein the length of the middle segment comprises a longitudinal axis; the plurality of carbon fiber plies are layered into a carbon fiber stack that provides at least a portion of a thickness of the middle segment; the carbon fiber stack comprises at least 8 carbon fiber plies; each carbon fiber ply of the carbon fiber stack comprises a stiffness, wherein the stiffness of each carbon fiber ply is determined by an orientation of carbon fibers within each carbon fiber ply relative to the longitudinal axis; the plurality of carbon fiber plies of the carbon fiber stack comprises a plurality of different orientations relative to the longitudinal axis, and thus the plurality of carbon fiber plies of the carbon fiber stack comprises a plurality of different stiffnesses; and the different orientations of the plurality of carbon fiber plies of the carbon fiber stack are self-symmetric or mostly self-symmetric through the thickness of the middle segment about a midpoint (400, 500, 600) of the carbon fiber stack, where the midpoint (400, 500, 600) is parallel to the longitudinal axis wherein the midpoint of the composite panel segment is the midpoint relative to the number of carbon fiber plies that make up the carbon fiber stack, wherein the term self-symmetric indicates that the plurality of carbon fiber plies that form the composite panel segment are mirror symmetric about the midpoint of the composite panel segment, and wherein, when mostly self-symmetric, the different orientations vary from being self-symmetric in no more than two carbon fiber plies wherein the longitudinal axis is oriented at 0°; wherein the different orientations of the plurality of carbon fiber plies include 0°, 45°, 90°, and -45° relative to the longitudinal axis of the middle segment, the middle segment has an axial modulus of elasticity of from about 78.6 GPa to about 92.4 GPa [11.4 megapounds per square inch (msi) to about 13.4 msi] and a Poisson's ratio of from about 0.38 to about 0.50; and from 46% to 58% of the plurality of carbon fiber plies are oriented at 0°.