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- Flight tests of thermal ice-prevention equipment on a Lockheed 12A airplane
- An analytical investigation of thermal-electric means of preventing ice formations on a propeller blade
- An Investigation of the Characteristics of Alcohol-Distribution Tubes Used for Ice Protection on Aircraft Windshields
- Tests of Thermal-Electric De-Icing Equipment for Propellers
- The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight
- The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight
- Comparison of Theoretical and Experimental Heat-Transfer Characteristics of Bodies of Revolution at Supersonic Speeds
- Wind-Tunnel Investigation at a Mach Number of 1.53 of an Airplane With a Triangular Wing
- Heat-transfer and boundary-layer transition on a heated 20 degree cone at a Mach number of 1.53
- Boundary-layer transition on a cooled 20 degree cone at Mach numbers of 1.5 and 2.0
- Comparison of theoretical and experimental heat transfer on a cooled 20 degrees cone with a laminar boundary layer at a Mach number of 2.02
- Damping in a roll of a missile configuration with a modified triangular wing and a cruciform tail at a Mach number of 1.52
- Lateral-Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable-Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52
- Lateral Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52
- Preliminary investigation of a variable-area auxiliary air-intake system at Mach numbers from 0 to 1.3
- Preliminary experimental investigation of a variable-area, variable-internal-contraction air inlet at Mach numbers between 1.42 and 2.44
- Preliminary Investigation of a Family of Diffusers Designed for Near Sonic Inlet Velocities
- Investigation of the Performance and Internal Flow of a Variable-Area, Variable-Internal-Contraction Inlet at Mach Numbers of 2.00, 2.50, and 2.92
- Viscous Flows in Inlets