Design and Investigation of a Transonic Axial-flow Compressor Rotor with an Inlet Hub-tip Radius Ratio of Essentially Zero

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Experimental Investigation of a Transonic Axial-flow-compressor Rotor Designed for Sonic Velocity with an Inlet Hub-tip Radius Ratio of 0.35

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Experimental Investigation of a 0.35 Hub-Tip Radius Ratio Transonic Axial Flow Rotor Designed for 40 Pounds Per Second Per Square Foot with a Design Tip Diffusion Factor of 0.20

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Experimental Investigation of a Transonic Axial-flow-compressor Rotor with Double-circular-arc Airfoil Blade Sections

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Performance of Single-stage Axial-flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and with Design Pressure Ration of 1.82

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Blade-element Performance of 0.7 Hub-tip Radius Ratio Axial-flow-pump Rotor with Tip Diffusion Factor of 0.43

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Performance of Single-stage Axial-flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1.19 and 1.26 Respectively, and with Design Pressure Ratio of 2.05

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Experimental Investigation of a 0.4 Hub-tip Diameter Ratio Axial-flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers

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Experimental Investigation of 0.35 Hub-tip Radius Ratiol Transonic Axial Flow Rotor Designed for 40 Pounds Per Second Per Square Foot with Design Tip Diffusion Factor of 0.20 [with List of References]

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Experimental Investigation of a 0.4 Hub-tip Diameter Ratio Axial-flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers

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