Introduction: "Because of the importance of the value of the transport mean free path of thermal neutrons in deuterium oxide, Kash and Woods proposed to redetermine this value in deuterium oxide (99.4 atom-percent deuterium, by an extrapolation method. Kash and Woods thought that the low value of the transport mean free path might be a source of error. This paper relates studies of procedures by which (1) boron material would be dissolved in high content deuterium oxide without adding foreign atoms, particularly hydrogen atoms which might adversely affect the test, (2) the boron content of the deuterium oxide solvent may be determined, (3) ion exchangers may be deuterized and de-deuterized, and (4) ion exchange may remove specific ions from solution."

"Free-flight drag measurements are presented which show the practicability of duplicating the zero-lift drag rise of many airplane configurations by simple bodies of revolution. The results confirm the transonic area rule for straight wings, and for delta and modified-delta wings with and without nacelles. The results showed that the area rule did not apply to one swept-wing configuration and an explanation is advanced to explain why it does not apply" (p. 1).

Report presenting an investigation to determine the effects of horizontal-tail location and plan form on the longitudinal stability and control characteristics of a fuselage and thin delta wing with extended double slotted flaps. Several configurations of the aircraft, including flaps with the tail off, extended double slotted flaps, and canard with extended double slotted flap and delta tail are explored.

"An investigation of the effect on transonic and supersonic drag of a fuselage protuberance designed to improve the overall longitudinal distribution of cross-sectional area of an essentially unswept wing-fuselage combination has been made with free-flight rocket models. The wing-fuselage configuration was tested with and without a fuselage protuberance designed to relieve the steep area gradient over the rear portion of the wing" (p. 1).