Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.

Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot deflector lateral control system installed ahead of the conventional ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the airplane and spoiler-slot-deflector effectiveness data were obtained through the complete angle-of-attack range with the ailerons neutral and with the ailerons drooped in conjunction with the normal flaps. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.

Report presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of conventional ailerons and operated as both individual units and combined segments. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.

Report presenting a full-scale wind-tunnel investigation to determine whether the effects of blowing high-velocity air over trailing-edge flaps could be adequately correlated by jet momentum over a range of jet velocities. Good correlation of lift with jet momentum was obtained over the range of jet pressure ratios.

Report presenting an investigation to determine the aerodynamic characteristics of a spoiler-slot-deflector configuration in combination with a trailing-edge 29-percent-chord high-lift flap. The wing has a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil. Results are also presented regarding the effect of deflector projection on the aerodynamic characteristics of a spoiler-slot-deflector on the plain wing.

Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio have been determined for Mach numbers of 1.97 and 3.33. The angle-of-attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. The results of the investigation indicate that there are distinct aerodynamic advantages to the use of highly swept wings of very low aspect ratio.

Transfer operations of highly radioactive solutions by the normal transfer pipette leads in most instances to a spread of contamination in the shielded facility. In the dripless pipette, the solution is held in the reservoir by the use of the siphon principle.