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- Investigation of the pressure-ratio requirements of the Langley 11-inch hypersonic tunnel with a variable-geometry diffuser
- An investigation of four wings of square plan form at a Mach number of 6.9 in the Langley 11-inch hypersonic tunnel
- An Investigation of Four Wings of Square Plan Form at a Mach Number of 6.86 in the Langley 11-Inch Hypersonic Tunnel
- An approximate method for determining the displacement effects and viscous drag of laminar boundary layers in two-dimensional hypersonic flow
- Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord
- Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-Wedge Sections With the Maximum Thickness at 0.18 Chord
- An Investigation of the Aerodynamic Characteristics of Thin Delta Wings With a Symmetrical Double-Wedge Section at a Mach Number of 6.9
- Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9
- Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9
- Effects of Boundary-Layer Displacement and Leading-Edge Bluntness on Pressure Distribution, Skin Friction, and Heat Transfer of Bodies at Hypersonic Speeds
- Boundary-Layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6