Browse TRAIL Inventories

An approximate method of calculating pressures in the tip region of a rectangular wing of circular-arc section at supersonic speeds

Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Preliminary investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61

Skin-friction drag and boundary-layer transition on a parabolic body of revolution (NACA RM-10)at a Mach number of 1.6 in the Langley 4-by-4 foot supersonic pressure tunnel

Factors affecting transition at supersonic speeds

Hinge-moment characteristics for several tip controls on a 60 degree sweptback delta wing at Mach number 1.61

Preliminary investigation of the effect of fences and balancing tabs on the hinge-moment characteristics of a tip control on a 60 degree delta wing at Mach number 1.61

Investigation of distributed surface roughness on a body of revolution at a Mach number of 1.61

Loads associated with spoilers at supersonic speeds

An investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61

Simplified procedures for estimating flap-control loads at supersonic speeds

Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01


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