Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7°

von Lewis, George W.
Veröffentlicht 1976

Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6

von Lewis, George W.
Veröffentlicht 1974

Aerodynamic performance of 0.5-meter-diameter, 337-meter-per-second tip speed, 1.5-pressure-ratio, single-stage fan designed for low noise aircraft engines

von Gelder, Thomas F.
Veröffentlicht 1974

Aerodynamic performance of a 1.20-pressure-ratio fan stage designed for low noise

von Lewis, George W.
Veröffentlicht 1976

Analytical and experimental performance of an explosion-cycle combustion chamber for a jet-propulsion engine

von Zipkin, Morris A.
Veröffentlicht 1948

Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle

von Lewis, George W.
Veröffentlicht 1974

Effects of three outlet-annulus area blockage configurations on the performance of a 20-inch (50.8-CM) axial-flow compressor rotor

von Osborne, Walter M.
Veröffentlicht 1969

Effects of reset stators and a rotating, grooved stator hub on performance of a 1.92-pressure-ratio compressor stage

von Lewis, George W.
Veröffentlicht 1977

Design and performance of a high-pressure-ratio, highly loaded axial-flow transonic compressor stage

von Lewis, George W.
Veröffentlicht 1974

Aerodynamic performance of 0.4066-scale model of JT8D refan stage with S-duct inlet

von Moore, Royce D.
Veröffentlicht 1977

Effects of several porous casing treatments on stall limit and an overall performance of an axial-flow compressor rotor

von Osborn, Walter M.
Veröffentlicht 1971

Performance of inlet stage of transonic compressor

von Urasek, Donald C.
Veröffentlicht 1976

Effect of casing treatment on performance of an inlet stage for a transonic multistage compressor

von Urasek, Donald C.
Veröffentlicht 1976

Performance of a low-pressure fan stage with reverse flow

von Moore, Royce D.
Veröffentlicht 1976

Performance of a transonic fan stage designed for a low meridional velocity ratio

von Moore, Royce D.
Veröffentlicht 1978

Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5°

von Lewis, George W.
Veröffentlicht 1976