This report covers a study of the deformation characteristics of uranium in grooved rolls. The study's purpose was to provide a basis for possible improvements in the uniformity of the rolled rod produced for the Hanford and Savannah River reactors.

This report follows work performed to determine the effects of large boron additions on the fabricability and room-temperature tensile properties of various steels for reactor shielding.

This report analyzes two high-current linear accelerators, the A-54--a 48.5 megacycle resonant cavity accelerator--and the A-48, that is under construction during the time this report is written.

The following report provides results from investigations of torsional vibration stresses in the drive shafts of two Westinghouse motor generator sets in 1952.

"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).

Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.

Report presenting a determination of the landing contact conditions of the Boeing B-47 airplane using a specially built motion picture camera. A statistical analysis of the sinking speeds and horizontal speeds was carried out on the photographs.

Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.

Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.

"An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).

Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.

Memorandum presenting a theoretical analysis of a cruciform missile configuration equipped with floating controls to determine if such controls can be utilized to improve the airframe transient response characteristics.The investigation covers either forward or aft locations of the floating controls at supersonic speeds. The results indicate that a substantial increase in airframe damping can be obtained through a proper selection of hinge-moment coefficients and through the use of a fixed-rate viscous damper attached to the floating-control surfaces.

Report presenting the aerodynamic loads acting over the vertical tail, which were determined during an investigation of the lateral stability and control characteristics of the Convair XF-92A. Results regarding the vertical-tail panel characteristics, vertical-tail load parameters, and vertical-tail bending and normal-force coefficients are provided.

Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.

Report presenting an investigation to determine the reverse-thrust performance of hemispherical target-type thrust reversers over a wide range of geometric variables. Several factors were found that increased the flow turn angle and reverse-thrust ratio, primarily the hemisphere diameter. Results regarding operating characteristics, relation of flow turn angle and reverse-thrust ratio, reverse-flow velocities and pressures along boattail, effect of boattail shape on reverse-thrust ratio, and modifications to hemispherical thrust reverser are provided.

"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).

Memorandum presenting an investigation of a low-speed leading-edge chord extension in the 19-foot pressure tunnel. Chord-extensions of various geometric designs were tested on three 45 degree sweptback wings of aspect ratio 5 and taper ratio 0.28 incorporating different airfoil sections. The data indicated that leading-edge chord-extensions could be used to produce large reductions in the longitudinal instability of all three wings tested.

Report discussing testing of a Hughes Falcon missile, C configuration, to determine the stability and control characteristics of the missile while rolling. Information about the time histories, normal force due to angle of attack, pitching moment due to angle of attack, damping, and control effectiveness is provided.

Report presenting the effects of inlet-air-flow distortion on the steady-state performance of a current axial-flow turbojet engine studied in an NACA altitude test chamber at a range of altitudes and simulated Mach number of 0.8. Radial distortions of various shapes up to 22 percent of the average engine-inlet total pressure and circumferential distortions up to 26 percent were imposed. Results regarding propagation through the engine, compressor-interstage performance and stall, effects on component performance, effects on overall engine performance, and effect on compressor blade vibration are provided.

Report presenting statistical measurements of landing-contact conditions for 144 landings of a heavy bomber airplane during routine daytime operations at Carswell Air Force Base. Using measurements obtained by a special photographic method, sinking speeds, bank angles, rolling velocities, and horizontal speeds at the instant before contact were evaluated and analyzed.

Report presenting an analysis of some strain-gage measurements of the loads carried by the wing and horizontal tail of a Boeing B-47A airplane during gradual-turn maneuvers for a variety of altitudes and Mach numbers. Results regarding the wing-load center of pressure, component loads, component-force coefficients, and fraction of the wing-fuselage load carried by the wing are provided.

Report presenting the results of an investigation showing the effect of the variation of taper ratio on the lift, drag, and pitching-moment characteristics of thin wings of aspect ratio 3 with 53.1 degrees of sweepback of the leading edge. Three wings with three different taper ratios in combination with a high-fineness-ratio body were studied.

Report presenting an investigation to determine the effect of both six- and eight-blade dual-rotation propellers on the internal-flow characteristics of an NACA 1-series D-type cowl and the effect of the cowl on the characteristics of the propellers.

Report presenting an investigation at Mach number 1.62 of a series of triangular wing and body combinations to determine the interference lift, drag, and pitching moment. Testing was conducted on seven flat-plate triangular wings of varying scale, four with a half-apex angle of 30 degrees and three with a half-apex angle of 45 degrees. Results regarding wing alone, wing in the presence of the body, basic quantities for interference evaluation, interference quantities, and contributions of both types of quantities are provided.