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- Test of NACA 66,2-116, a =0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
- Investigation in the Langley 19-foot pressure tunnel of two wings of NACA 65-210 and 64-210 airfoil sections with various type flaps
- Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section.Transonic-bump method
- Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925
- Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925
- 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
- Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section.Transonic-bump method
- Effects of compressibility on lift and load characteristics of a tapered wing of NACA 64-210 airfoil sections up to a Mach number of 0.60