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- An investigation of several NACA 1-series nose inlets with and without protruding central bodies at high-subsonic Mach numbers and at a Mach number of 1.2
- Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing
- Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35©�, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section.Transonic-bump method
- Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components
- Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range
- Aerodynamic characteristics of a leading-edge slat on a 35 degree swept-back wing for Mach numbers from 0.30 to 0.88
- 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
- Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds
- Combustion of aluminum borohydride in a supersonic wind tunnel
- The rolling moment due to sideslip of swept wings at subsonic and transonic speeds
- An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds
- Initial experimental investigation of the aerodynamic load on the wing of a model caused by a blast-induced gust that increases the angle of attack into the stall region
- Experimental aerodynamic forces and moments at low speed of a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage combination
- Some factors affecting the variation of pitching moment with sideslip of aircraft configurations
- 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
- A wind-tunnel investigation of the development of lift on wings in accelerated longitudinal motion
- Wind-tunnel investigation of damping in roll at supersonic speeds of triangular wings at angles of attack
- Wind-tunnel investigation of the static longitudinal and lateral stability of a 1/62-scale model of the X-1E at supersonic speeds
- Effects of two leading-edge modifications on the aerodynamic characteristics of a thin low-aspect-ratio delta wing at transonic speeds
- Transonic investigation of aerodynamic characteristics of a swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches
- Low-speed static stability characteristics of a cambered-delta-wing model
- Investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections
- 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
- Aerodynamic characteristics of a spoiler-slot-deflector control on a 45©� sweptback wing at Mach numbers of 1.61 and 2.01
- Investigation of the aerodynamic characteristics in pitch and sideslip of a 45©� swept-wing airplane configuration with various vertical locations of the wing and horizontal tail.Static lateral and directional stability; Mach numbers of 1.41 and 2.01
- Transonic wind-tunnel investigation of aerodynamic-loading characteristics of a 2-percent-thick trapezoidal wing in combination with basic and indented bodies
- Wind-tunnel investigation of effects of ventral fins at two positions on lateral-stability derivatives of 45©� high-wing model oscillating in yaw
- Steady loads due to jet interference on wings, tails, and fuselages at transonic speeds
- 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