A common and useful assumption is that the front-to-rear power distribution is a shortened cosine curve. This fact led to the calculation of slug factors'' for the longer charges to be used at K-Pile. It is hoped that the publication of these numbers will save time and prevent duplication of effort by those concerned in any way with slug power, surface temperatures, reactivity effects, etc. For the sake of completeness, slug factors for the older piles are included. Another useful ideal is that tube power distributions can be approximated by the assumption of a cylindrical pile and a cosine distribution of power outside of a central flattened region. This led to another double set of numbers since the values for the 2004 tube piles were again included for completeness. 2 figs., 6 tabs.

Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.

Memorandum presenting a study of the ignition of ammonia and mixed oxides of nitrogen at 160 degrees Fahrenheit made with and without fuel additives utilizing small-scale rocket engines of approximately 200 pounds thrust. All experiments were conducted at sea-level pressures except two at a range of pressure altitudes. Results regarding the use of lithium as a catalyst, calcium as a catalyst, and no apparent catalyst are provided.

From Introduction: "In reference 1, in which the performance of conical supersonic scoop inlets on circular fuselages is reported, the drag of the bottom-inlet configuration was considerably higher than for the top inlet."

"The performance of liquid fluorine and liquid ammonia as a propellant combination was evaluated in 1000-pound-thrust rocket engines operated at a chamber pressure of 600 pounds per square inch absolute. Values of specific impulse, characteristic velocity, thrust coefficient, and heat rejection were obtained as functions of propellant mixture ratio for each of four injectors: a triplet, a showerhead, and two like-on-like types" (p. 1).

Report presenting a study of four short annular diffusers with different diffuser passage area variations and with various combinations of straightening vanes, vortex generators, splitters, and boundary layer suction for flow control. Results regarding turbine discharge whirl, diffuser passage modification, and boundary layer control are provided.

Report presenting an experimental investigation to determine the effect of several wedge-type boundary-layer diverters on drag and inlet pressure recovery in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.5, 1.8, and 2.0. The model consisted of two rectangular ramp-type inlets mounted on the NACA RM-10 body of revolution. Results regarding variation of inlet pressure recovery and configuration drag with inlet mass-flow ratio, changes in the shock pattern off the inlet ramp, pressure-recovery-mass-flow characteristics, and drag coefficients are provided.