Technical report. From Abstract : "Magnetic moment measurements have been made on single crystals of terbium (hcp) with fields of 50 to 18,000 oe applied along the <1120> (a-axis), <1010> (b-axis), and <0001> (c-axis) directions. The temperature range covered was 1.4 to 500°K."

Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.

From introduction: A subsurface exploration program was undertaken to investigate the concentration of uranium and vanadium in or near the base of the Shinarump member of the Chinle formation in the Flatirons locality, and to develop criteria whereby adjacent unexplored areas could be evaluated as to potential production capacity from study of geological and mineralogical features at the host rook outcrop. An earlier study of the area by C. G. Evensen of the U. S. Atomic Energy Commission had shown that geological conditions favorable to the accumulation of commercial uranium deposits were present in the Flatirons area.

Report discussing testing to determine the effects of control profile on the dynamic hinge-moment and flutter characteristics of a trailing-edge flap-type control. A conventional control and two control profile modifications were examined. Information about spring moments is also provided.

Memorandum presenting a flight investigation using pulse techniques to determine longitudinal and lateral dynamic stability characteristics of the D-558-II research airplane with particular reference to the jet exhaust effects of the rocket engine. Results regarding the longitudinal stability characteristics, and lateral stability characteristics are provided.

Report presenting measurements of the skin temperature and surface pressure on a large-scale, highly polished nose with a relatively sharp-tipped 100 degree total-angle cone followed by a conical flare section of 10 degree half-angle. Heating on the forward 3.0 to 4.5 inches of the 100 degrees cone was generally lower than that on the rearward portion.

Report presenting an investigation of the hydrodynamic characteristics of a multijet water-based aircraft capable of supersonic speeds and with jet engines exhausting through the step. The step engine exhausts were found to considerably increase afterbody wetting and smooth-water resistance, but they had no significant effect on longitudinal stability. Results regarding spray characteristics, resistance and stability at constant speed, take-off stability, landing stability, and jet noise are provided.

Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.

Study conducted for the U. S. Army Reactors Branch of reactors for the irradiation of food.

Report wherein acid free uranyl nitrate hexahydrate was distributed into 4-1/2 percent TBP-Amsco 125-90W and combined with various concentrations of acid in order to study the distribution of uranium and hydrolysis effects.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations on the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Results regarding accuracy and remarks on effects of stores are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of the addition of one body-mounted external store, tip tanks, and several tip-mounted missile configurations on the aerodynamic characteristics in pitch of a fighter model with a low-aspect-ratio, unswept wing at Mach number 1.82. Many of the tip-mounted store configurations were found to produce increased lift-curve slopes and drag increments which decreased with increasing lift coefficient above lift coefficients of about 0.06.

Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.

Report presenting a wind-tunnel investigation at low speed in the 300 mph 7- by 10-foot tunnel to determine the effect of deflector projection on the control effectiveness of spoiler-slot-deflectors on a 30 degree sweptback wing-fuselage model equipped with either a 15-percent-chord spoiler or a spoiler-slot-deflector. Results regarding the aerodynamic characteristics, wing longitudinal characteristics, rolling-moment characteristics, and pressure distributions are provided.

Report presenting an investigation in the high-speed tunnel using the transonic bump technique in order to study the effectiveness of full-span flap-type controls on 31 unswept rectangular wings. Results regarding lift-curve slope, flap-effectiveness parameter, and the agreement between predicted and experimental results are also provided.

Document HW-33176, "A Proposed Scope of the 100-K Sulfuric Acid Addition Facilities", presented the justification and bases for a sulfuric acid addition facility at the 183-K headhouses and included a system for adding the acid to the raw water. Since the issue of this document several factors to consider in such a system have been brought to light by experience gained both at K and at other areas. The alternate system presented here eliminates several of the troublesome points in the previously proposed system.

Report presenting a study of the application of Wiener filter theory to the design of a beam-rider guidance system operating in the presence of glint noise. The theory is then used to establish the theoretical lower limit of root-mean-square error and the corresponding desired transfer-function characteristics.

Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.

Report presenting a procedure for estimating the range of peak airplane load factors and maneuvering tail loads likely to be experienced in pitch-up maneuvers. Results of computations indicated that though the load factors and maneuvering tail loads were not critical in pitch-up maneuvers at 35,000 feet, they were likely to exceed design levels at 15,200 feet.

Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.

Report presenting a wind-tunnel investigation on two series of twisted and cambered wings, which were identical except for wing section, to compare the effects of NACA 4-digit and NACA 64A chordwise distributions of thickness on the longitudinal aerodynamic characteristics of the wings. Results regarding the low-speed results, high-speed results, and flow studies are provided.

Memorandum presenting the effects of resin coating methods on some physical properties of laminates prepared with glass fabric, Fiberglas 181, and bonded with two commercial polyester resins. The resins used were Laminac 4126 and Selectron 5003. The resin coating methods used were roller coating, application of a dilute solution of resin, resin immersion, application of monomeric styrene, and vacuum impregnation.

A brief summary is made of methods available to the helicopter designer for obtaining desired stability characteristics by modifications to the airframe design. The discussion is based on modifications made during the establishment of flying-qualities criteria and includes sample indications of theoretical studies of additional methods.

"Altitude performance characteristics of the J65-B3 turbojet engine and its components were obtained at engine-inlet conditions corresponding to Reynolds number indices from 0.2 to 0.8 over a range of corrected engine speeds from 70 to 110 percent of rated speed. Engine operational limits up to an altitude of 75,000 feet together with ignition and windmilling characteristics were also obtained. The engine and component data are presented both in graphical and in tabulated form. The operational characteristics are presented in graphical form" (p. 1).