Memorandum presenting the results of a free-jet investigation to determine the internal performance of a 16-inch ram jet. Data were obtained at a range of altitudes and Mach numbers. Results regarding the rake flame holder, effect of fuel injector on burner performance, effect of propylene oxide on burner performance, serrated annular baffle flame holder, diffuser performance, and performance at off-design spike location are provided.

Surge characteristics of the XJ34-WE-32 turbojet engine were determined over a range of altitudes. Several typical oscillograph traces during which surge occurred are presented. The effect of altitude on the surge line and it's relation to the steady-state operating region are shown.

From Introduction: "This report also presents a method of optimizing the blade number and solidity for a given application if the blade loss variation with solidity can be estimated or experimentally determined. Also discussed are the penalties in performance that accompany deviations from optimum values of blade number and solidity."

Report presenting an investigation of the effect of first-stator area changes on the overall component performance of the J71-97 experimental turbine. The performance of the turbine with the first-stator area reduced to 70 percent of design by reorienting the stagger angle of the design blade profiles is presented. Results regarding the overall performance, choking characteristics, and matching characteristics are provided.

Data were calculated for equivalence ratios of 1 to 4, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperatures, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance for a wide range of chamber pressures. A method for obtaining specific impulse of JP-4 fuel with OF2 and O3-F2 mixtures is given.

Report presenting pressure distribution associated with the stable combustion of aluminum borohydride about a body of revolution in a wind tunnel at Mach number 2.47. Pressure increases on the cylindrical and base surfaces of the model were measured. Results regarding the burning and associated flow phenomena, axial and meridional static-pressure data obtained during combustion, and base-pressure data during combustion are provided.

From Summary: "Nine divergent-shroud ejector configurations were investigated to determine the effect of shroud divergence angle on ejector internal performance. Unheated dry air was used for both the primary and secondary flows. The decrease in the design-point thrust coefficient with increasing flow divergence angle (angle measured from primary exit to shroud exit) followed very closely a simple relation involving the cosine of the angle. This indicates that design-point thrust performance for divergent-shroud ejectors can be predicted with reasonable accuracy within the range investigated."

From Summary: "Use of a normal-shock positioning control was demonstrated at Mach numbers of 1.8 and 2.0 for a translating-spike supersonic inlet in combination with a J34 turbojet engine. Stable operation of the control was obtained which can be partly attributed to a nonlinearity in the servo valve in the null region."

Static tests were made on the compatibility of liquid fluorine with several nonmetallic materials at -3200 F and at pressures of 0 and 1500 pounds per square inch gage. The results are compared with those from previous work with gaseous fluorine at the same pressures, but at atmospheric temperature. In general, although environmental effects were not always consistent, reactivity was least with the low-temperature, low-pressure liquid fluorine. Reactivity was greatest with the warm, high-pressure gaseous fluorine.