From Summary: "As part of an overall program for the experimental investigation of large-scale jet nozzles, a preliminary evaluation of the internal performance characteristics of several variable-throat extended-plug-type nozzles was obtained over a range of nozzle pressure rations from 2 to 15 with nozzle throat variations as great as 2:1. The extended-plug nozzle attained peak thrust coefficients as high as those which have been attained with fixed-geometry convergent-divergent nozzles. The thrust coefficients of the extended-plug nozzles were relatively insensitive to both nozzle pressure ratio and throat area over the range investigated."

"The explosion limits of five alkylsilanes were determined as a function of temperature and composition at a pressure of 1 atmosphere. Over a fuel concentration range of 2 to 10 percent, the lowest temperatures (zero C) below which explosion did not occur for the five fuels studied were: tetramethylsilane (CHsub3)sub4Si, 450 degrees; trimethlysilane (CHsub3)sub3SiH, 310 degrees;dimethylsilane (CHsub3)sub2SiHsub2, 220 degrees; methylsilane CHsub3SiHsub3, 130 degrees; and vinylsilane Hsub2C=CH-SiHsub3, 90 degrees. Explosion limits for hydrocarbons analogous to these silanes fall in a temperature range of 500 degrees to 600 degrees C" (p. 1).

Report presenting zero-lift drag data obtained on a series of eight fin-stabilized bodies with noses of fineness ratio 3 and differing nose shape by launching them from a helium gun. The nose shapes explored included a cone, x exp(3/4), x exp(1/2), parabolic, (3/4)P, (1/2)P, L-V Haack, and Von Karman. The results are compared with theoretical calculations and wind-tunnel measurements.

Report of an investigation to determine the effects of inboard plan-form modifications on two unswept wings at Mach numbers 1.61 and 2.01. The only difference between the two wings was the spanwise thickness distribution. The modifications were performed by means of inserting sections that linearly extended the local chord from the 40 percent semispan station to the model center line.

Report presenting an investigation on a full-scale afterburner test rig and two turbojet-engine afterburner configurations to determine criteria for the design of fuel systems for afterburners. The effect of fuel-air ratio distributions at the flame holder on combustion performance was obtained along with the effects of variation in design variables on the ratio distributions.

"The flame velocities were measured of 20 percent oxygen and 80 percent carbon monoxide mixtures containing either light water or heavy water. The flame velocity increased from 34.5 centimeters per second with no added water to about 104 centimeters per second for a 1.8 percent addition of light water and to 84 centimeters per second for an equal addition of heavy water. The addition of heavy water caused greater increases in flame velocity with equilibrium hydrogen-atom concentration than would be predicted by the Tanford and Pease square-root relation" (p. 1).

From Summary: "Total vapor pressures were measured for 16 acid mixtures of the ternary system nitric acid, nitrogen dioxide, and water within the temperature range 10 degrees to 60 degrees Celsius, and with the composition range 71 to 89 weight percent nitric acid, 7 to 20 weight percent nitrogen dioxide, and 1 to 10 weight percent water. Heats of vaporization were calculated from the vapor pressure measurements for each sample for the temperatures 25, 40, and 60 degrees Celsius. The ullage of the apparatus used for the measurements was 0.46. Ternary diagrams showing isobars as a function of composition of the system were constructed from experimental and interpolated data for the temperatures 25, 40, 45, and 60 degrees C and are presented herein."

Abstract: "The cross section for this reaction is calculated for three Hulthen deuteron wave functions. A hard core in the deuteron at one-half meson Compton wavelength reduces the total cross section and flattens the angular distribution in the backwards direction in agreement with experiment."

Description of cooling, shielding, controls are discussed for 100 kw and 1 Mw operation of a low cost experimental neutron chain reactor.