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- Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925
- 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
- The Influence of a Change in Body Shape on the Effects of Twist and Camber as Determined by a Transonic Wind-Tunnel Investigation of a 45 Degree Sweptback Wing-Fuselage Configuration