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- Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components
- Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans
- Tests at Mach Number 1.62 of a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces
- An Investigation at Mach Numbers of 1.62 and 1.93 of the Lift Effectiveness and Integrated Downwash Characteristics of Several In-Line Missile Configurations Having Equal-Span Wings and Tails
- The Use of the Rolled-Up Vortex Concept for Predicting Wing-Tail Interference and Comparison With Experiment at Mach Number of 1.62 for a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces
- Investigation of Reynolds Number Effects for a Series of Cone-Cylinder Bodies at Mach Numbers of 1.62, 1.93, and 2.41
- An Investigation of the Effects of Jet Exhaust and Reynolds Number Upon the Flow Over the Vertical Stabilizer and Rudder of the Douglas D-558-II Research Airplane at Mach Numbers of 1.62, 1.93, and 2.41
- Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-Inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93