From abstract: "The relative differential neutron-proton scattering cross section has been measured in the range of center-of-mass angles from 5.1° to 36.0° for approximately 90-Mev neutrons and from 10.7° to 37.8° for approximately 290-Mev neutrons."

The following report proposes a concept of a transient version of Astron thermonuclear reactor while describing the basic concepts of the reactor and the design criteria.

This report presents a description of and operating instructions for APOTA--a device which automatically tracks any signal-emitting source within the 190 to 250 MC band. APOTA is especially useful for telemetering applications.

This technical report provides a design criteria for a technical support facility for the Lithium Cooled Reactor Experiment (LCRE) and SNAP-50-DR-1 Test Facilities. The support facility is adjacent to the LCRE Test Facility and is located completely within the existing Building 629 structure at the former ANP area of the National Reactor Testing Station (NRTS) near Idaho Falls, Idaho. The information and specifications presented establish the basis for the design of laboratories, shops and engineering areas required to support the installation, operation, maintenance and disassembly of the LCRE and SNAP-50 tests. The construction and modification required to adapt the building to reactor test support operations are described in detail in the following report.

A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.

A discussion of pertinent items related to the design of internal-flow systems for reciprocating engine, turbine engine, and pressure-jet installations in helicopters. The following items are emphasized: controllable exit and ram recovery for reciprocating-engine cooling, performance penalties possible in turbine-engine installations, the effects of high subsonic flow velocities on the performance of duct elements, and the effects of centrifugal forces on the flow in a ducted helicopter rotor.

Report presenting the pressure distribution over a highly swept wing at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for this investigation had 63 degrees of sweepback of the leading edge, an aspect ratio of 3.5, and a taper ratio of 0.25. Over the regions influenced by the wing tip and trailing edge, the effects of viscosity apparently are responsible for the poorer agreement between theory and experiment.

Report presenting the first results of pressure measurements obtained on a fuselage and a 45 degree sweptback wing-fuselage combination at transonic speeds in the slotted test section of the 8-foot high-speed tunnel. The test was part of a systematic investigation of varying amounts of sweepback on wings suitable for transonic flight. Results regarding the wing, fuselage, and fuselage with wing are provided.

Report presenting an investigation conducted with several 73-percent semispan inboard spoiler ailerons, projecting 4 percent of the local wing chord from the wing surface, and located at the 70-percent chord line of a 45 degree sweptback wing-fuselage combination. Results regarding the effect of upper-surface spoilers on basic model characteristics, effect of gap on spoiler characteristics, comparison of upper- and lower-surface spoiler characteristics, comparison of upper-surface spoiler with oppositely deflected spoilers, effect of Mach number on spoiler effectiveness, and a comparison of spoiler effectiveness with aileron effectiveness are provided.

Report presenting an investigation of a constant-area, circular 90 degree elbow of mean radius of curvature equal to its diameter with several arrangements of simple, nontwisted, rectangular vortex generators. The inlet flow had a boundary layer of about one-tenth the duct diameter. Results regarding an elbow with no vortex generators and an elbow with vortex generators are provided.

The results of an analytical investigation of the theoretical air specific impulse performance and adiabatic combustion temperatures of several possible ram-jet fuels over a range of equivalence ratios, inlet-air temperatures, and combustion pressures, is presented herein. The fuels include octane-1, 50-percent-magnesium slurry, boron, pentaborane, diborane, hydrogen, carbon, and aluminum. Thermal effects from high combustion temperatures were found to effect considerably the combustion performance of all the fuels. An increase in combustion pressure was beneficial to air specific impulse at high combustion temperatures. The use of these theoretical data in engine operation and in the evaluation of experimental data is described.

Report presenting testing of the effectiveness of transpiration cooling of an 8 degree total angle conical body with water removed onto the surface through a porous section near the nose. Results regarding a reference test without cooling, a cooling test with 0.010 pound of water per second, a cooling test with 0.0025 pound of water per second, a hypothesis of the phenomena of liquid transpiration cooling, water consumption are provided.

Report presenting data for five diffusers tested with and without vortex-generator controls in order to determine the performance improvements attainable through the use of boundary-layer controls. Results regarding inlet conditions, axial inlet flow, and whirling inlet flow are provided.

"An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight" (p. 1).

Report presenting an investigation of the effect of yaw and angle of attack on the total-pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet designed to have low external drag at a Mach number of 2.7 and an angle of attack of 0 degrees. Total-pressure recovery and mass-flow data are presented for a Mach number of 2.71 at angles of yaw 0, 2.5, and 5 degrees and angles of attack of 0 and 5 degrees are provided.

Conclusions from the study: "Radioactive dusts are carcinogenic, and can cause cancer of the lung. complete dose response curves have not yet been determined. All the parameters that render this demonstrably toxic material (radioactive dust) have not yet been evaluated. It is strongly suggested by the experimental data that duration of radiological insult to the lung is an important factor in eliciting lung cancer. The atmospheric tolerance concentrations now in use seem to afford little margin of safety."

The designer's concept of a test program for the 30-Mw prototype intermediate heat exchanger and steam generator designed and fabricated as part of the Sodium Components Development Program is presented. The performance data will serve to verify the thermal design, or allow application of improved techniques to future designs, give an improved basis for stress analysis in design of future units, and demonstrate the capability and limitations of the units in relation to the performance specifications for which they were designed. Welding techniques for type 316 stainless steel are described. The specifications and operating conditions of the units are given along with instrumentation drawings showing test equipment design and arrangement.

With the assumption of infinite conductivity a simple model may be constructed for the dynamic construction of a current carrying plasma, i.e., the pinch effect. The magneto-hydrodynamic equations of this model are discussed and solved. It is also shown that the infinite conductivity model can be derived from a picture of particles orbiting without collisions in the fields set up by their motions.

Report presenting an investigation in the transonic blowdown tunnel to obtain static longitudinal force and moment characteristics of two wings, one with an aspect ratio of 1.73 and 3-percent-thick delta wing and one with an aspect-ratio-1.73 4-percent-thick clipped delta wing mounted on a slender body. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

Report discussing the problem of point-to-point radio communication on the moon. Equations and curves are presented to estimate power requirements in lunar communication systems. Consideration is given to ground wave attenuation over both layered and non-layered grounds, antenna ground losses in situations where ground screens are impractical, noise level estimates in the receiving system, and the effects on propagation of possible lunar ionospheres. An example of the calculation of required power for a particular communication system is given, and further studies are suggested.

The performance of NACA 65-series compressor blade sections in cascade has been investigated systematically in a low-speed cascade tunnel.

Report presenting an investigation of the handling qualities of a fighter airplane that is controlled by a pilot supplying signals to a rate type of automatic control system. The handling qualities were investigated in pull-ups, aileron rolls, aerobatics, rough-air flying, and precision tasks.

An analysis is presented of the relationship of various engine factors to knock in preignition in an aircraft engine. From this analysis and from the available experimental data, a method of evaluating the knocking characteristics of the fuel in an aircraft-engine cylinder is suggested.

"An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).