16 and the airfoil surface 4 the composite blade 2 is constructed by initially laying composite laminate 16 on the spar 8 at a surface 10 in a spanwise direction from above the blade base plane 5 downward toward the spar root 12 the directionality of the composite laminate 39 s fibers may be determined as is widely known and practiced by those skilled in the art the composite laminate 16 is then guided through the spaced recesses 13 located within the spar root 12 the composite laminate 16 is then wrapped essentially 180 degrees around these arcuated recesses 13 located at the base of the spar root 12 the composite laminate 16 then routed back in a spanwise fashion to a surface 10 on the spar 8 above the blade base plane 5 this composite laminate 16 is then compressed and cured according to the current art the composite blade 2 thus provides a mechanical joint between the composite laminate 16 and the spar root 12 whereby the composite laminate 16 as wrapped about the radially inward arcuate surfaces 20 of the spar root 12 opposes centrifugal and other stresses as previously discussed in detail the depths and chordwise widths of the recesses 13 are calculated in terms.