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- Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area
- Investigation of Turbines for Driving Supersonic Compressors: 1: Design and Performance of First Configuration
- Effect of Certain Combinations of Wall Contouring and Design Exit Velocity Distribution on Prediction of Turbine-Nozzle Mass Flow
- Investigation of Turbines for Driving Supersonic Compressors 5: Design and Performance of Third Configuration With Nontwisted Rotor Blades
- Investigation of Turbines for Driving Supersonic Compressors 3: First Configuration With Four Nozzle Settings and One Nozzle Modification
- Investigation of Turbines for Driving Supersonic Compressors 4: Design and Performance of Second Configuration Including Study of Three-Dimensional Flow Effects
- Effect of Reduced Stator-Blade Trailing-Edge Thickness on Over-All Performance of a Transonic Turbine
- Effect of a reduction in stator solidity on performance of a transonic turbine
- Use of effective momentum thickness in describing turbine rotor-blade losses
- Analysis of turbomachine viscous losses affected by changes in blade geometry
- Experimental Investigation of Turbine Stator-Blade-Outlet Boundary-Layer Characteristics and a Comparison With Theoretical Results
- Analysis of two-stage-turbine efficiency characteristics in terms of work and speed requirements