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- 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