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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
- Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds
- Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section.Transonic-bump method