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- Aerodynamic characteristics of a wing with quarter-chord line swept back 35©�, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section.Transonic-bump method
- A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel
- Tests of a small-scale NACA submerged inlet at transonic Mach numbers
- An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47©� sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel
- Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45©� sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds number from 1 x 10⁶ to 8 x 10⁶
- An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds
- Transonic wind-tunnel investigation of the effects of sweepback and thickness ratio on the wing loads of a wing-body combination of aspect ratio 4 and taper ratio 0.6
- Effects of wing-body geometry on the lateral-flow angularities at subsonic speeds
- Transonic investigation at lifting conditions of streamline contouring in the sweptback-wing-fuselage juncture in combination with the transonic area rule
- A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring
- Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies
- Transonic wind-tunnel investigation of aerodynamic-loading characteristics of a 2-percent-thick trapezoidal wing in combination with basic and indented bodies
- Effect at high subsonic speeds of fuselage forebody strakes on the static stability and vertical-tail-load characteristics of a complete model having a delta wing