A structural composite airfoil having a leading edge and a trailing edge , the structural composite airfoil comprising: a primary structural element extending from a leading edge region to a trailing edge region , wherein the leading edge region is adjacent the leading edge of the structural composite airfoil, wherein the primary structural element comprises: an upper skin panel ; a lower skin panel ; an internal volume defined between the upper skin panel and the lower skin panel; and a front C-channel spar comprising an upper flange coupled to the upper skin panel, wherein the front C-channel spar further comprises a lower flange coupled to the lower skin panel, wherein a first channel of the front C-channel spar faces the leading edge of the structural composite airfoil, wherein the upper flange forms a first angle with an elongated span of the front C-channel spar, wherein the lower flange forms a second angle with the elongated span, and wherein the first angle is acute; a secondary structural element defining the trailing edge of the structural composite airfoil; a leading edge skin panel defining the leading edge of the structural composite airfoil and positioned adjacent the leading edge region of the primary structural element, wherein a first end region of the leading edge skin panel is coupled to the upper flange of the front C-channel spar, wherein a second end region of the leading edge skin panel is coupled to the lower flange of the front C-channel spar, and wherein the leading edge skin panel has a bullnose shape; and a trailing edge closeout cover , wherein: a first cover end region of the trailing edge closeout cover is bonded to the lower skin panel, and the first cover end region of the trailing edge closeout cover is recessed into the lower skin panel; and a second cover end region of the trailing edge closeout cover comprises an integral wedge coupled to the upper skin panel. an upper skin panel ; a lower skin panel ; an internal volume defined between the upper skin panel and the lower skin panel; and a front C-channel spar comprising an upper flange coupled to the upper skin panel, wherein the front C-channel spar further comprises a lower flange coupled to the lower skin panel, wherein a first channel of the front C-channel spar faces the leading edge of the structural composite airfoil, wherein the upper flange forms a first angle with an elongated span of the front C-channel spar, wherein the lower flange forms a second angle with the elongated span, and wherein the first angle is acute; a secondary structural element defining the trailing edge of the structural composite airfoil; a leading edge skin panel defining the leading edge of the structural composite airfoil and positioned adjacent the leading edge region of the primary structural element, wherein a first end region of the leading edge skin panel is coupled to the upper flange of the front C-channel spar, wherein a second end region of the leading edge skin panel is coupled to the lower flange of the front C-channel spar, and wherein the leading edge skin panel has a bullnose shape; and a trailing edge closeout cover , wherein: a first cover end region of the trailing edge closeout cover is bonded to the lower skin panel, and the first cover end region of the trailing edge closeout cover is recessed into the lower skin panel; and a second cover end region of the trailing edge closeout cover comprises an integral wedge coupled to the upper skin panel. a first cover end region of the trailing edge closeout cover is bonded to the lower skin panel, and the first cover end region of the trailing edge closeout cover is recessed into the lower skin panel; and a second cover end region of the trailing edge closeout cover comprises an integral wedge coupled to the upper skin panel. <EOS>