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- Pressure Measurements on a Sharply Converging Fuselage Afterbody With Jet on and Off at Mach Numbers From 0.8 to 1.6
- Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5
- Pressure Distributions at Mach Numbers From 0.6 to 1.9 Measured in Free Flight on a Parabolic Body of Revolution With Sharply Convergent Afterbody
- Some Experimental Effects of Afterbody Shape on the Zero-Lift Drag of Bodies for Mach Numbers Between 0.8 and 1.3
- Transonic Drag Measurements of Eight Body-Nose Shapes
- Transonic Zero-Lift Drag Tests of Four Equivalent-Body-of-Revolution Models Representing Variations of the Convair F-102 Airplane
- Zero-Lift Drag of a Series of Bomb Shapes at Mach Numbers From 0.60 to 1.10
- Local Heat Transfer to Blunt Noses at High Supersonic Speeds
- Heat Transfer Measured on a Flat-Face Cylinder in Free Flight at Mach Numbers Up to 13.9
- Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14