Gas turbine engine

A gas turbine engine comprising:

• a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches, the turbine section having a low pressure turbine comprising a stage count (N) defined by a number of rows of rotating blades of the low pressure turbine;
• an unducted fan driven by the turbomachine, the unducted fan having a plurality of blades arranged in a single row and defining a blade tip diameter (D) in feet;
• a gearbox coupled to the low pressure turbine and the unducted fan, the gearbox having a gear ratio (GR);
• and
• an engine correlation parameter that is greater than 0.17 and less than 0.83, wherein the engine correlation parameter equals D/N/GR;
• wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific thrust determined as follows:
• FnTotal×EGT/(AHPCExit2×1000).