Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.

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.

Abstract: "Drill hole UCe-18 was successfully logged with the U.S. Geological Survey-La Coste Romberg borehole gravity meter to a depth of 6,488 feet. That density increases with depth is apparent in both the alluvium and volcanic rock. The in situ density of the alluvium measured by the gravity meter ranges from 1.77 to 2.34 gm/cc; the lake beds beneath the alluvium have a density of 2.22 gm/cc; and the rhyolitic rocks range in density from 2.26 to 2.47 gm/cc. The average density determined from the borehole gravity meter data for the alluvium plus the lake beds is 2.22 gm/cc and for the volcanic rocks is 2.35 gm/cc."

From Abstract: "Comparisons with other intensity measurements in individual spectra indicate that the National Bureau of Standards spectral-line intensities may have average errors of 20 percent, but first of all they provide uniform quantitative values for the seventy chemical elements commonly determined by spectrochemists. These data are presented by element in part I, and all 39,000 observed lines are given in order of wavelength in part II."

This is the sixteenth quarterly report of the research and development activities of the Radiological Sciences Department, Hanford Atomic Products Operation, as before, includes some items charged to control but included for general interest. Such are identified as "not charged to research."

In this report we present solutions of the design problem in which a system of quadruple lenses is required to carry a particle beam from given focal lines in the x and y planes to other given focal lines. Particular attention will be given to the case of the anastigmatic lens system which takes a beam from one focal point to another focal point. Since the general problem is almost impossibly complicated a simplification is introduced by breaking the lens system into two parts. The first part of the lens system is required to bring the initial beam to the state where it is parallel to the z axis in both planes. The second part carries the initially parallel beam to the required final condition. Each part will involve two quadrupoles so that the complete system will consist of four quadruples; usually, however, the field gradients in the second and third quadrupoles can be made identical so that those quadrupoles can be combined into one and the system becomes a three quadrupole system. The configuration of the lens element will be as shown in the figures below. These figures indicate also the general character of the beam path in the …

Report on sea-level performance tests of a 22-inch-diameter pulse-jet engine on a thrust stand. The tests were conducted at several ram pressures and the entire range of fuel flows that the engine can operate at. Information about the maximum-thrust operation, operating frequency, maximum combustion chamber pressures, and operating lives is provided.

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."

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 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.

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.

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: "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."

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."

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.

This quarterly progress report discusses in detail the work done by the Analytical Chemistry Division at Oak Ridge National Laboratory. In particular, this report discusses the research and development work ongoing at the X-10 Site and the Y-12 Site.

An air cored pulse deflection coil has been constructed for the Brookhaven AGS. The system produces a deflecting pulse with a peak radial deflection of 2.5 cms and duration of 70 microseconds. Beam spill duration of 15 to 50 microseconds from the target is readily achieved. One deflector has given satisfactory service for over a year and a second unit has been installed this summer.