Report presenting an investigation of the effect of combustion on diffusion in the fuel preparation zone of a ram-jet engine. The information was applied in the design of combustor to operate at lean fuel-air ratios.

Report presenting a solution for the two-group equations for reflected thermal reactors of spherical geometry for constant power generation over the reactor-core volume. Solution is obtained both analytically and by means of an electrical analogue simulator.

Report presenting a low-speed investigation of the static longitudinal aerodynamic characteristics of a twisted and cambered wing with 45 degrees of sweepback and an aspect ratio of 8.0 in the 19-foot pressure tunnel. Testing included the effects of leading- and trailing-edge flaps, flow control fences, and a fuselage. Report presenting longitudinal stability characteristics, lift characteristics, drag characteristics, fuselage effects, Reynolds number effects, effect of wing roughness are provided.

From Introduction: "The purpose of the investigation conducted at the NACA Lewis laboratory and reported herein was to determine the improvements possible in full-scale turbojet-engine performance when a single-annular combustor with slotted air-inlet orifices was used."

Memorandum presenting an investigation of the static aerodynamic and dynamic damping-in-roll characteristics of an aircraft rocket with cruciform fins of trapezoidal plan form as determined experimentally at a range of Mach numbers. The fins had tow holes cut through each fin panel, and the effects of the holes or slots were investigated by testing with both solid and slotted fins.

Report presenting an investigation of the longitudinal control effectiveness of a full-chord wing-tip control surface on a wing with 35 degrees of sweepback, 12 percent thickness perpendicular to the quarter-chord line, an aspect ratio of 3.01, and a taper ratio of 0.605 at a range of Mach numbers. Wing-tip control was only 1/6 as effect in producing pitching moment at subsonic speeds as a flap type control and 1/2 as effect at low-supersonic speeds.

Report presenting an investigation of the overall performance of a 20-inch-tip-diameter 10-stage compressor as the initial step to examine the problems encountered in an axial-flow compressor with a high pressure ratio per stage. The investigation was carried out over a range of weight flows and percentages of the design speed. Results regarding the part-speed efficiency, surge characteristics, overspeed characteristics, compressor discharge Mach number, and stage characteristics are provided.

Memorandum presenting a simplified analysis to determine the effective thermal conductivity of a powder from the fraction of space occupied by the gas and conductivities of the solid and the gas which make up the powder. Tests were conducted to determine the conductivity of magnesium oxide powder in various gases at a range of temperatures. The effects of some of the factors neglected in the simplified analysis, such as bending of the heat-flow lines and the irregularity of the arrangement of the particles, were investigated and discussed.

From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques previously used, a secondary flow of cooling air was provided around the afterburner shell."

Report presenting a flight investigation to determine the zero-lift drag characteristics of a twin-engine supersonic ramjet configuration in order to make performance calculations below the design Mach number. Data was obtained over a range of Mach numbers for two power-off ramjet models with and without nacelles. Information about the variation of Reynolds number, total and external drag coefficients, and model-component drag coefficients is provided.

From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."

Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form.

"The object of the research project described herein is to present the design basis for test apparatus to determine the heat-transfer and pressure-drop characteristics of white fuming nitric acid flowing in a heated tube section. The heat flux to the tube will be of the order of magnitude occurring in a regeneratively cooled rocket engine" (p. 1).

Memorandum presenting a supplementary investigation conducted in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement upon the spin and spin-recovery characteristics of a 1/20-scale model of the McDonnell F2H-3 airplane. Results regarding the tests with wing-tip tanks installed and with the experimental aerodynamic shape installed are provided.

This report presents the results of an investigation conducted in the Langley free-flight tunnel to determine the effects of large artificial variations of several rotary lateral-stability derivatives on the dynamic lateral stability and control characteristics of a 45 degree sweptback-wing airplane model. Calculations of the period and damping of the lateral motions and of the response to roll and yaw disturbances were made for correlation with the experimental results. The calculated results were in qualitative agreement with the experimental results in predicting the general trends in flight characteristics produced by large changes in the stability derivatives, but in some cases the theory with the assumption of zero lag was not in good quantitative agreement with the experimental results.

"A theoretical method is derived for the determination of the motions and loads during chine-immersed water landings of prismatic bodies. This method makes use of a variation of two-dimensional deflected water mass over the complete range of immersion, modified by a correction for three-dimensional flow. Equations are simplified through omission of the term proportional to the acceleration of the deflected mass for use in calculation of loads on hulls having moderate and heavy beam loading" (p. 1025).

Report presenting an investigation to determine the effects of two types of propeller-spinner junctures on the pressure-recovery characteristics of an NACA 1-series D-type cowl with an NACA 1-series spinner, in combination with a four-blade single-rotation propeller.

Foreword: This report covers one part of a comprehensive study to determine the relationship between the trafficability of soils and the mobility of military vehicles.

Abstract: Zeunerite occurs near the surface of a granite stock on the southwest flank of Brooks Mountain, Alaska. The largest deposit is at the Foggy Day prospect where zeunerite is disseminated in hematite which partially or totally fills openings and vugs in a highly oxidized lensshaped body of pegmatitic granite and to a minor extent in openings and cracks in the weathered granite enclosing the lens. Although a few specimens from the pegmatitic lens contain as high as 2.1 percent equivalent uranium, the overall average content of the lens rock is between 0.1 and 0.2 percent equivalent uranium and about 0.07 percent equivalent uranium for both the lens material and the surrounding zeunerite-bearing granite.

From abstract: The land-pebble phosphate district of Florida is a part of the Gulf Coastal Plain. The geologic formations cropping out in the district are the Miocene Hawthorn, Pliocene Bone Valley, and Pleistocene terrace sands. The Bone Valley formation consists of a lower strongly phosphatic unit and an upper less phosphatic unit. This paper is concerned principally with the lower unit, which contains the bulk of the minable phosphate deposits of the district.

Abstract: Reconnaissance for uranium in the Lost River area, Seward Peninsula, Alaska, during the 1951 field season revealed the presence of minor amounts of radioactive material in mineralized portions of rhyolitic dikes and in a small iron-enriched zone in limestone. The dikes contain as much as 0.01 percent equivalent uranium locally and average 00005 percent equivalent uranium. The radioactive material occurs as a secondary hematitic coating of the dike rock. The iron-enriched zone has an average content of about 0.06 percent equivalent uranium with the radioactive material occuring in limonite, hematite, goethite, and mimetite. The radioactivity of these minerals is due to the presence of uranium as an impurity. No uranium deposits of economic importance were found.

A study of the density of aqueous uranyl solutions is described which was had as its primary purpose the development of an analytical method for the determination of uranium in relatively dilute solutions of this salt. These solutions contain trace amounts of contaminating elements. The presence of small amounts of free sulfuric acid and moderate variations in the temperature at which density measurements are made can be compensated for by the use of equations provided for the calculation of uranium concentration.

None

Report discussing different types of uranium deposits found in Colorado mines and the geological guides which can help locate these deposits.