compressor 14 highly compressed air is delivered to combustor 16 combustion gases 44 from combustor 16 propel turbines 18 and 20 high pressure turbine 18 rotates second shaft 28 and high pressure compressor 14 while low pressure turbine 20 rotates first shaft 26 and low pressure compressor 12 about axis 32 during some engine operations such as during takeoff operations and other operating periods when engine power output is relatively high fan 38 rotates such that a radially outer portion of blades 40 attains supersonic velocity as a result the supersonically rotating portions of blades 40 may produce shockwaves which can be heard as noise the noise may be spread over a broad tonal range from many multiples of blade passing frequency down to the disk rotational frequency fig2 is an exploded perspective view of an exemplary composite blade 100 and fan rotor disk 102 that may be used with gas turbine engine 10 a plurality of circumferentially spaced blades 100 are supported by rotor disk or drum 102 through a dovetail slot 104 each blade 100 includes an airfoil 106 that extends between a dovetail root 108 and a blade tip 110 such that each blade 100 is supported through dovetail root 108 and dovetail slot 104 by rotor 102 blade 100 is representative of the plurality of circumferentially spaced blades 100 that are each mapped into a specific slot 104 based on measured parameters of blade 100 in the exemplary embodiment each blade 100 includes a composite.