A gas turbine engine includes a turbomachine comprising a turbomachine defining a working gas flowpath and an inlet to the working gas flowpath; a fan having a fan blade formed of a composite material, the fan blade defining a leading edge fan radius RFan_LE and a trailing edge fan radius RFan_TE, and the fan defining a leading edge hub radius RHub_LE and a trailing edge hub radius RHub_TE, the gas turbine engine defining a bypass ratio during operation of the gas turbine engine in a cruise operating mode; and a speed reduction device mechanically coupling the turbomachine to the fan; wherein the gas turbine engine defines a fan leading edge to trailing edge compression factor (FLTCF) or a fan leading edge to trailing edge opening ratio (FLTOR). The FLTCF is greater than or equal to 1.05 and less than or equal to 1.8.