From abstract: "The deposit on the rods is in the form of a brittle uneven tube which is cracked off and subsequently pulverized to a 200-mesh powder. This report is chiefly concerned with methods of consolidating this powder and shaping it into forms required, though it also discusses to some extent other methods of shaping boron or born-rich materials."

From summary: "This report covers an experimental investigation into the fabrication of various potential fuel-element materials and the testing of these materials for compatibility with structural metals at 1090 C (2000 F)."

From abstract: "The inert-gas metal-arc welding process was used to determine weldability studies of various aluminum alloys that are being considered for use as can materials. The solid-phase and induction welding processes were also investigated for making can closures."

This report discusses the concept of an improved mass gauging technique with a scintillation counter as the radiation detector in order to meet industrial requirements.

Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.

Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.

Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.

Memorandum presenting an analysis made of the probable range of the stability parameters of present and future missiles. Included is a short review of the dynamic theory and some of the factors and assumptions influencing the stability derivatives and equations of motion.

Report presenting the use of a flush-type electrical pressure cell for measuring rapidly changing aerodynamic forces on a fluttering control surface. The use of the cell is valuable for the measurement of the aerodynamic forces. Results regarding the individual cells, integrated results, resolution of aerodynamic moments, comparison of aerodynamic with inertia moments, and comparison of static and dynamic hinge moments are provided.

"The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio" (p. 1).

"Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the one with a 7-percent-thick circular-arc airfoil section" (p. 1).

"The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).

Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.

Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.

"Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration are presented. The range of Mach numbers considered includes those cases for which the wing and tail surfaces have subsonic leading edges, supersonic leading edges, and combinations of the two. The methods of analysis are discussed; these represent detailed consideration of the important effects and contributions of the various airplane components utilizing available theories and theoretically justifiable and reasonable approximations" (p. 1).

From Introduction: "The rolling-pullout maneuver (any maneuver in which rolls occur during high g flight conditions) has been shown to be pertinent to design considerations from the standpoint of the loads produced on a vertical tail (refs. 1 to 3). In order to understand this problem better, the results of an analytical study of effects of large variations of some of the lateral-stability-derivative coefficients on the maximum angle of sideslip at first peak of its oscillation are presented in this paper. Also, expressions for estimating the effects of small variations of or errors in these coefficients on the maximum sideslip angle have been developed and are presented. "

Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduction of adverse effects of propellers on longitudinal stability, and propulsive characteristics are provided.

This report follows an investigation with the purpose of studying the operational characteristics of a catalytic tube recombiner where the gases are passed over stainless steel tubes coated with platinum black.

The gas commonly used in the chamber of the Simpson Proportional Alpha Counter (ASP) is the high grade, 99% pure methane. The cost of the gas has often raised the question of finding an adequate substitute and a number of substitutions have been attempted. Commercial methane has been substituted successfully for 99% pure methane and its use is recommended in ASP counters. Neither commercial nor technical methane caused any significant changes in instrument operation.

The method of detecting unpaired electrons in liquid and solid systems by electron spin resonance is discussed. The significance of the hyperfine structure in electron spin resonance is discussed and the possible use of these structural features of the electron spin resonance spectrum to elucidate the nature of the photoproduced unpaired electrons in photosynthesizing systems is introduced.

Brief description of new species of ground squirrels, Evotomys, Marten, Molossus, prairie dog, kangaroo rats, pocket gopher, and Hesperomys.

Investigation of the performance of Inconel 739 (a nickel-base alloy of low critical-element content) buckets in a J33-9 engine showed that Inconel 739 had an engine life at least equivalent if not superior to S-816 buckets operated at 1500 degrees F. Inconel 739 buckets had a small scatter in life and exhibited lower total elongation than S-816. Bucket life was less than that predicted on; the basis of stress-rupture considerations alone. The failure mechanism was probably influenced by fatigue.

From Introduction: "The object of this report is to investigate the effects of after-burner lighting on the engine behavior and control-system requirements of a controlled turbojet engine. In this report, a simulation procedure for the afterburner is developed (based on ref. 3), this afterburner simulation is coordinated with previously developed nonafterburning-engine simulation procedures (ref. 4), and the compensated interacting control systems of references 1 and 2 are used. The results of an analog investigation of the the effects of an afterburner light on several controlled turbojet-engine configurations are reported and evaluated."

Memorandum presenting an investigation conducted in the 27- by 27-inch preflight jet of the release characteristics of a dynamically scaled AVCO booster vehicle, internally carried store model from a scale simulated bomb bay of the B-52 airplane at Mach numbers of 0.64 and 0.93. Simulated altitudes were -11,800 feet and 50,000 feet. Successful releases were obtained at all Mach numbers and simulated altitudes of the test.