greater than about 2 3 in one disclosed embodiment the gas turbine engine 20 includes a bypass ratio greater than about ten 10 1 and the fan diameter is significantly larger than an outer diameter of the low pressure compressor 44 it should be understood however that the above parameters are only exemplary of one embodiment of a gas turbine engine including a geared architecture and that the present disclosure is applicable to other gas turbine engines a significant amount of thrust is provided by the bypass flow b due to the high bypass ratio the fan section 22 of the engine 20 is designed for a particular flight condition u2014 typically cruise at about 0 8 mach and about 35 000 feet the flight condition of 0 8 mach and 35 000 ft with the engine at its best fuel consumption u2014 also known as u201c bucket cruise thrust specific fuel consumption u2018 tsfc u2019 u201d u2014 is the industry standard parameter of pound mass lbm of fuel per hour being burned divided by pound force lbf of thrust the engine produces at that minimum point u201c low fan pressure ratio u201d is the pressure ratio across the fan blade alone without a fan exit guide vane u201c fegv u201d system the low fan pressure ratio as disclosed herein according to one non limiting embodiment is less than about 1 50 in another non limiting embodiment the low fan pressure ratio is less than.