Memorandum presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.

Report presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The airfoil section was designed to have favorable pressure gradients between the suction slots. Results indicated that the laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the surface condition as has been observed in other similar investigations.

Report presenting an investigation in the transonic tunnel to determine the effects of varying Reynolds number on the pressure distribution on a transonic body of revolution at angles of attack through the transonic speed range. The effect of change in sting cone angle on the pressure distributions and a comparison of experimental incremental pressures with theory is also provided.

From Summary: "From a theory developed on a quasi-one-dimensional-flow basis, it was found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow were presented. The theory developed in the report was in agreement with the experimental data of the reports both of Sterbentz and Evvard and of Ferri and Nucci."

"At subsonic speeds the pressure drag arising from the thickness of the body or wings is negligible so long as the shapes are sufficiently well streamlined to avoid flow separation. In that range there exists no possibility of either favorable or adverse interference on the pressure distributions themselves. If one body is so placed as to receive a drag from the pressure field of another then the second body is sure to receive a corresponding increment of thrust from the first" (p. 1).

Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.

Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.

Memorandum summarizing the lift and drag characteristics of a series of five low-aspect-ratio triangular-wing or modified triangular-wing airplane models. The series consists of three triangular wings of aspect ratios 2, 3, and 4 and two modified triangular wings of aspect ratio 2 with taper ratios of 0.20 and 0.33. The experimental lift and drag characteristics of the five models are compared with existing theory.

Report presenting an experimental investigation to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4 using a zero-lift rocket-propelled model in free flight. Results regarding the variation of the aileron floating angle, the wing-tip helix, the balancing effect, and the penalty occurred throughout the Mach number range are provided.

Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.

Memorandum presenting an investigation of the stability and controllability in space of an arrangement comprising a man standing on a small platform which is rigidly connected to a jet nozzle with its thrust axis perpendicular to the platform and its thrust opposed to the pull of gravity. Results regarding the initial flights with the platform, flights with landing gear, flights with landing gear and inertia, flights with landing gear and gyroscope, flights with landing gear and control stick, flights with landing gear and seat, and discussion of the balancing process are provided.