Browse TRAIL Inventories

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

A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel

Tests of a small-scale NACA submerged inlet at transonic Mach numbers

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

Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45©� sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds number from 1 x 10⁶ to 8 x 10⁶

An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds

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

Transonic investigation at lifting conditions of streamline contouring in the sweptback-wing-fuselage juncture in combination with the transonic area rule

Effects of wing-body geometry on the lateral-flow angularities at subsonic speeds

A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring

Transonic wind-tunnel investigation of aerodynamic-loading characteristics of a 2-percent-thick trapezoidal wing in combination with basic and indented bodies

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

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


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