Report presenting the effect of preinjection-fuel temperature on vaporization rates and combustion efficiency of a 16-inch ram-jet engine for two different fuels. Variation of the location of the fuel injectors and use of control sleeves were also explored.

Monthly report documenting Imperial Sugar operational expenses for the year, broken down by actual sales and production, with estimated operational numbers for the remainder of the year.

Report presenting an investigation of a 15 degree semiangle movable-cone variable-geometry ram-jet inlet to determine the variable-geometry effect on total-pressure recovery at free-jet Mach numbers of 1.62, 2.00, 2.53, and 3.05 at zero angles of attack and yaw. Generally, increasing the cowling-position parameter increased the value of both total-pressure recovery and mass-flow ratio. Results regarding the total-pressure recovery, shadowgraphs, and total-pressure recovery as a function of free-stream Mach number are provided.

Annual report from C. Lamar Wallis to Harris L. Kempner and board of trustees outlining general points of interest regarding the Rosenberg Library, such as remodeling, increases in use, changes in staff, needs and prospects for the upcoming year.

Report discussing an impinging experiment "to test the pitting tendencies of different qualities of water," specifically, alum coagulated water without sodium dichromate, alum coagulated water plus 2 ppm sodium dichromate, and ferrifloc coagulated water without sodium dichromate.

A device has been designed which will support small spheres and cylinders in a vacuum system during a plating operation. While supporting the object to be plated, the device automatically shifts the position of the supports so that the coating is evenly distributed. This report describes the mechanism by which this motion is achieved.

Memorandum presenting the application of the concept of indicial functions to the analysis of the aerodynamic phenomena associated with the short-period pitching mode of wings in subsonic and supersonic flight. Simple physical relationships are pointed out and are used to study the effect on the rotary-damping-moment coefficient of changes in center-of-gravity position, Mach number, aspect ratio, plan form, frequency, and thickness.

Memorandum presenting an investigation in the supersonic blowdown tunnel to determine the effects of span and spanwise and chordwise location on the control characteristics of spoilers on a 6-percent-thick, 50 degrees sweptback wing of aspect ratio 2.5 and taper ratio of 0.625. The results of the investigation indicate that the inboard spoilers located at the rearward chordwise station produce the highest rolling-moment effectiveness.

Report for the Imperial Sugar Company describing the estimated daily cash balances for the company.

Report presenting a simplified limiting-blade-loading parameter for axial-flow-compressor blade elements derived from the application of a separation criterion used in two-dimensional boundary-layer theory to a typical suction-surface velocity distribution of a compressor blade element at design angle of attack. Results regarding two-dimensional cascade, compressor rotors, and compressor stators are provided.

The results of electrical resistance measurements have been used as a means of following changes occurring in metals due to irradiation. The electrical conductivity is sensitive to changes in composition and to cold-work or structure damage. In an anisotropic metal, such as uranium, the director of measurement also influences to some extent the values obtained. For these reasons it is essential to use the same material, and if possible the same piece of material, in comparing the electrical properties before and after irradiation. This report is a description of the measurements made on pieces of the same uranium rod before and after an exposure of approximately 150 MWD/T. The results, while preliminary in nature and dealing only with one sample and exposure level, provide data for which a comparison may be made of the electrical resistivity of irradiated and non-irradiated uranium metal.

Report presenting information on landing gear applied drag loads and the nature of wheel spin-up in landing based on testing in the Langley impact basin. Particular attention is paid to the nature and variation of the coefficient of friction between the tire and runway during the wheel spin-up process. Results regarding the fundamentals of the process, comparison of maximum loads, variation of coefficient of friction, and effect of prerotation are provided.

Report presenting an experimental investigation at Mach number 1.90 to determine the effect of a diverter-type boundary-layer removal system on the performance of a scoop inlet. The supersonic portion of the inlet consisted of a two-dimensional, reverse Prandtl-Meyer turn followed by a constant-area throat. Results regarding the effect of fuselage position and subsonic diffuser performance are provided.

Report presenting an investigation to determine the effects of a horizontal tail on the longitudinal stability characteristics of a swept-back, twisted, and cambered wing in combination with a fuselage and various combinations of high-lift and stall-control devices. The ideal placement of the horizontal tail appeared to be at 6 percent wing semispan below the wing-root-chord plane.

Report presenting an experimental investigation of the application of transpiration air-cooling to the combustion-chamber wall of an afterburner. Results regarding the typical temperature and pressure profiles, correlation of wall temperatures, distribution of cooling-air flux density, longitudinal distribution of cooling air, longitudinal distribution of wall temperature, effect of permeability on cooling-air requirements, and fabricating and operating problems are provided.

From Summary: "A summary has been made of the available experimental data on division of normal-force loads between the wing and fuselage of aircraft. Comparison of the experimental values with theoretical calculations which include interference effects shows good agreement in general with the greatest differences occurring near a Mach number of 1.0. At high angles of attack, above the range of linear lift curves, the proportion of the total wing-fuselage load carried by the wing decreases and this effect occurs throughout the subsonic- and transonic-speed region."

Abstract: "The ductility of Type 310 stainless steel T-joints brazed with GE-62 brazing alloy was measured at room temperatures 1200, 1650, and 1800 F. The measure of ductility was taken as the plastic axial strain required to crack braze fillets in T-section tensile specimens. At elevated temperatures, the ductility of as-brazed joints approximated that of the stainless steel, but at room temperature the brazed joints had only one-tenth the ductility of the base metal. Annealing for 16 hr at 1800 F in air was found to triple the room-temperature ductility of the brazed joint."

Report presenting an investigation of the flow properties of a constant-outer-wall annual diffuser in combination with a tailpipe in order to come up with a configuration suitable for turbojet afterburners. Information about axial inlet flow and whirling inlet flow is provided. During testing, a vena contrata region formed downstream from the center body terminal and rendered the first 1/2 diameter of the tailpipe ineffective.

From Summary: "A method is presented for calculating the lift and centers of pressure of wing-body and wing-body-tail combinations at subsonic, transonic, and supersonic speeds. A set of design charts and a computing table are presented which reduce the computations to routine operations. Comparison between the estimated and experimental characteristics for a number of wing-body and wing-body-tail combinations shows correlation to within + or - 10 percent on lift and to within about + or - 0.02 of the body length on center of pressure."

Abstract: A device is proposed for confining charged particles to a localized region of space by means of the alternating electric field of a resonant cavity. The motion of single electrons in the field is stable. The limitations to particle density and temperature are discussed, and found to be too severe to allow the device to serve as a reactor, although it might be a useful laboratory tool.

"The relation of Whitcomb's "area rule" to the linear formulas for wave drag at lightly supersonic speeds is discussed. By adopting an approximate relation between the source strength and the geometry of a wing-body combination, the wave-drag theory is expressed in terms involving the areas intercepted by oblique planes or Mach planes. The resulting formulas are checked by comparison with the drag measurements obtained in wind-tunnel experiments and in experiments with falling models in free air. Finally, a theory for determining wing-body shapes of minimum drag at supersonic Mach numbers is discussed and some preliminary experiments are reported" (p. 757).

Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.

A preliminary study of positive pion production from proton-nucleus collisions revealed that positive pion production cross sections agree more favorably with a Z 2/3 variation than with a variation proportional to the atomic number. A similar study on negative pion production has shown that negative pion yields from proton-nucleus collisions tend to vary in proportion to the number of neutrons in the nucleus. As a result an experiment was performed to investigate if there is a significant change in positive pion production with changing atomic number at two lower pion energies.

External-drag data are presented for normal-shock nose inlets with NACA 1-series, parabolic, and conic cowling profiles. The tests were made at an angle of attack of 0 degrees by using rocket-propelled models in free flight at Mach numbers from 0.9 to 1.5. The Reynolds number based on body maximum diameter varied from 2.5 x 10 sup 6 to 5.5 x 10 sup 6.