Aircraft Propulsion

afterbody afterburning aircraft airflow airplane amplitude angle of attack augmentor ball bearing blade loading bleed boattail boundary layer bypass bypass ratio centerbody coefficient combustion combustor compressor compressor stall configuration coolant coolant flow cooling air cowl CTOL curve diffuser downstream drag duct dynamic effect efficiency engine inlet experimental film cooling flight frequency fuel hertz increase inlet pressure inlet temperature inlet unstart installed Investigation lift lift coefficient liquid methane loss lubricant Mach number methane NASA TM obtained operating percent performance plug nozzle polyphenyl ether pressure ratio primary problem propulsion system radial distortion range reduced region seal shock position shown in figure shows slot stage stall limit stall margin static pressure stator steady-state STOL subsonic SUPERSONIC CRUISE supersonic transport surface takeoff tank terminal shock tests throat tip speed total pressure trailing edge turbofan turbojet vane velocity VTOL wing