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- Investigation of X24C-2 10-Stage Axial-Flow Compressor 2: Effect of Inlet-Air Pressure and Temperature of Performance
- Investigation of 10-Stage Axial-Flow X24C-2 Compressor, 1, Performance at Inlet Pressure of 21 Inches Mercury Absolute and Inlet Temperature of 538 Degrees R
- Effect of First-Stage Blade Design on Performance of Mark 25 Torpedo Power Plant
- Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Nozzles and Three Rotor-Blade Designs
- Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 2 - Efficiency with 20 Degrees-Inlet-Angle Rotor Blades
- Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 1 - Efficiency with 0.45-inch Rotor Blades
- Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 3: Efficiency with Standard Rotor Blades
- Summary of Investigations of Mark 25 Aerial-Torpedo Turbine
- 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
- Component Performance Investigation of J71 Type II Turbines 5 - Internal Flow Conditions of J71 Type IIA Turbine
- Component Performance Investigation of J71 Type II Turbines 3 - Overall Performance of J71 Type IIA Turbine
- Component Performance Investigation of J71 Experimental Turbine 3 - Effect of Third-Stage Shrouding on Over-All Performance
- Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine
- Component Performance Investigation of J71 Experimental Turbine 9 - Effect of First-Stator Adjustment;Internal Flow Conditions of J71-97 Turbine With 87-Percent-Design Stator Area