Report discussing studies testing various thorium alloys consisting of either Ames thorium and up to 5% of various additions or Ames thorium and up to 50% uranium. Effects of molybdenum additions for fusion welding, and cold-work strengthening were also tested. Methods, experimental data, and discussion is included.

"An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability" (p. 1).

Report presenting an investigation of the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.39, 1.60, and 1.98. A streamline store, a blunt-nose store with wedge-type fins of low aspect ratio, and a bluff store with a skirt were tested. Results regarding pitching motions, ejection velocity, effect of increase in altitude, and addition of plate or spike to the nose of the store are provided.

Report presenting flight measurements of the aerodynamic wing normal force, bending moment, and pitching moment using strain gains on the D-558-II airplane at Mach numbers up to 0.87 and angles of attack up to 38 degrees. Results regarding Mach number effects and normal-force-coefficient effects are provided.

Report discussing the spin and spin-recovery characteristics of a model of the Douglas X-3 airplane in a free-spinning tunnel. The pitching-moment characteristics of the scale model were not found to be typical of larger scale results. The results indicated that at an altitude range of 15,000 to 30,000 feet, the X-3 will not exhibit unusual trim tendencies and it will be difficult to obtain erect spins unless the ailerons are full with the spin.

Report presenting an investigation in the high-speed tunnel of a 42.7 degree sweptback wing model to determine the effects of aileron trailing-edge thickness on aileron hinge moments and one-degree-of-freedom aileron flutter. Results regarding the hinge-moment characteristics and free-floating characteristics are also provided.

One of the techniques by which highly ionized plasmas can be generated in the laboratory makes use of strong, electromagnetically driven shock waves propagating into a cold gas. In this paper the phenomenon is analyzed as a one-dimensional single-fluid hydromagnetic problem, neglecting dissipation behind the wave.

This is a preliminary report on the magnetic measurements taken to date on the AGS experimental magnets. It mainly summarizes the results which were necessary for the setting up of the proton separated beam in August 1961. A few curves on information obtained since then are included. When the study is finished, a complete report on all phases of the work, including the methods used, will be forthcoming.

An additive mechanism of micro- and macro-convective heat transfer was formulated to represent boiling heat transfer with net vapor generation to saturated, non-metallic fluids in convective flow. The final equations are [equations not transcribed]. The second equation will be recognized as the Dittus-Boelter equation with the additional factor F. The two functions F and S are defined as [equations not transcribed] where Re is the effective Reynolds number for the two-phase fluid and ΔTe is the effective superheat for bubble growth. F and S were obtained as functions of the Martinelli parameter and the two-phase Reynolds number, respectively. The correlation was tested with available data for water and organic fluids. Data from different sources which could not be satisfactorily correlated by existing correlations were shown to be quite well correlated by the one presently proposed. The average deviation between calculated and measured boiling coefficients for all data points from nine experimental cases was ±11%

Report discussing measurements of viscosity made with relative viscometers. These instruments must be calibrated with liquids whose viscosities are known. NBS provides a series of 10 oils for this purpose. Their viscosities range from 0.02 to 450 poises and their temperature coefficients of viscosity range from 2.1 to 9.4 percent per degree C. The less viscous oils are more stable. Correction formulas for errors or conditions are presented.

From Summary: "An investigation was conducted in the 6- by 6-foot test section of the Langley stability tunnel on a modified Koppers Aeromatic wind-driven impeller-generator combination. This investigation consisted of a few fixed pitch tests and a series of variable pitch tests. The fixed pitch tests indicated that the impeller should operate between the blade-pitch angles of 20 and 32deg at the specified output of 11.7 kilowatts in order to remain within the specified rotational speed of from 5000 to 8000 rpm for airspeeds of from 130 to 175 miles per hour. The requirement that the impeller maintain rotational speeds of - between 5000 and 8000 rpm as the impeller output varied from 0 to ll.7 kilowatts at airspeeds of from 130 to 175 miles per hour was not met at any time during the variable pitch tests."

Report presenting an investigation to determine flight behavior after ejection from a bomb bay of several dynamically scaled bluff internal stores for a range of Mach numbers and altitudes. The trajectories of all of the stores were smooth, but the pitching motions of the stores were greatly affected by the close vicinity of the bomb bay. Types of stores explored included WADC stores, flared-cylinder stores, and cylindrical stores.

Memorandum presenting the aerodynamic loading on delta wings at supersonic speeds, which was studied primarily to determine the coupling and nonlinear interference effects between the pressures due to angle of attack and due to thickness. Results regarding span loadings and lift coefficients, pressure distributions due to thickness, pressure distributions due to angle of attack and interference pressures produced by thickness, and Reynolds number effects are provided.

Memorandum presenting an investigation in the 27- by 27-inch preflight jet on the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.30, 1.60, and 1.98. A model of a typical fighter-bomber airplane with high sweptback wings was used. Results for streamline store A, blunt-nose store B, and bluff store C are provided.

This research on the pressure variations in the injection system of the N.A.C.A. Spray Photography Equipment and on the effects of these variations on the motion of the timing valve stem was undertaken in connection with the study of fuel injection systems for high-speed oil engines. The methods of analysis of the pressure variations and the general equation for the motion of the spring-loaded stem for the timing valve are applicable to a spring-loaded automatic injection valve, and in general to all hydraulically operated valves. A sample calculation for a spring-loaded automatic injection valve is included.

"An investigation of the 19XB-2A gas turbine is being conducted at the Cleveland laboratory to determine the effect on turbine performance of various inlet pressures, inlet temperatures, pressure ratios, and wheel speeds. The engine of which this turbine is a component is designed to operate at an air flow of 30 pounds per second at a compressor rotor speed of 17,000 rpm at sea-level conditions. At these conditions the total-pressure ratio is 2.08 across the turbine and the turbine inlet total temperature is 2000 degrees R" (p. 1).