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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

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

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 Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections

Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components

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

Aerodynamic characteristics of a leading-edge slat on a 35 degree swept-back wing for Mach numbers from 0.30 to 0.88

Aerodynamic characteristics in pitch of several triple-body missile configurations at Mach numbers 0.6 to 1.4

Factors affecting the maximum lift-drag ratio at high supersonic speeds

A wind-tunnel investigation of the development of lift on wings in accelerated longitudinal motion

Lift-curve slopes determined in flight on a flexible swept-wing jet bomber

Effects of wing inboard plan-form modifications on lift, drag, and longitudinal stability at Mach numbers from 1.0 to 2.3 of a rocket-propelled free-flight model with a 52.5 degree sweptback wing of aspect ratio 3


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