Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.

"A program of creep-rupture tests of several bars of Beryllium has been completed. The tests were made at 1200, 1400, 1550, and 1700 F. in protective atmospheres of tank helium or hydrogen. The results are given in a summary table and by creep and design curves. A description of the test set-up is included."

Report presenting a wind-tunnel investigation of an external store of fineness ratio 8.6 on the chord plane of several low-aspect-ratio wings. Testing occurred at a Mach number of 1.9 on wings with 60 degree leading-edge sweepback and unswept trailing edges with taper ratios of 0 and 0.28 and on an unswept wing with a taper ratio of 0.625. Results regarding the loading breakdown, store position, and effect of store on control characteristics are provided.

From introduction: "It has become desirable to develop an alternative method for the determination of lithium to serve as a stand-by method at times when the flame photometer is inoperative, or to supplement the latter in cases where a doubtful analysis requires further investigation. A method based upon the precipitation of lithium with potassium ferriperiodate was investigated because of its expected freedom from interference by aluminum."

The first part of this quarterly progress report details reactor theory and design, discussing the aircraft reactor experiment, experimental reactor engineering, reactor physics, and critical experiments. The second part of this report is not included. The third part of this quarterly progress report details materials research, discussing corrosion research, physical properties and heat-transfer research, metallurgy and ceramics, chemistry of high-temperature liquids, and radiation damage. The fourth part of this quarterly progress report details alternate systems, discussing a supercritical water reactor, circulating-moderator-coolant reactors. The fifth part of this quarterly progress report includes appendixes.

Report presenting an investigation at subsonic speeds to determine the effects of lip shape and entrance Mach number on the characteristics of a scoop-type air-induction system designed for an airplane flying at supersonic speeds. Results regarding the ram-recovery ratio, static-pressure distribution, and drag are provided.

Technical report focusing on the Homogeneous Reactor Experiment (HRE) construction, completed 60% as of August 15, 1951. Report also includes alternate systems studies and long range studies of the Homogeneous Reactor Experiment. Technical report is organized in three parts. [From Summary]

"Ignition delay determinations of several fuels with nitric oxidants were made at simulated altitude conditions utilizing a small-scale rocket engine of approximately 50 pounds thrust. Included in the fuels were aniline, hydrazine hydrate, furfuryl alcohol, furfuryl mercaptan, turpentine, and mixtures of triethylamine with mixed xylidines and diallyaniline. Red fuming, white fuming, and anhydrous nitric acids were used with and without additives. A diallylaniline - triethylamine mixture and a red fuming nitric acid analyzing 3.5 percent water and 16 percent NO2 by weight was found to have a wide temperature-pressure ignition range, yielding average delays from 13 milliseconds at 110 degrees F to 55 milliseconds at -95 degrees F regardless of the initial ambient pressure that ranged from sea-level pressure altitude of 94,000 feet" (p. 1).

"An experimental investigation is being conducted at the Lewis laboratory to establish general principles for the design of noncritical turbine rotor configurations. This investigation includes evaluation of cooling effectiveness, structural stability, cooling-air flow distribution characteristics, and methods of supplying cooling air to the turbine rotor blades. Prior to design of a noncritical rotor, a standard turbine rotor of a commerical turbojet engine was split in the plane of rotation and machined to provide a passage for distributing cooling air to the base of each blade" (p. 1).

In recent months, experiments investigating the total, non-elastic, transport, etc., cross-sections of U-238 have been performed. It is the purpose of this memo to examine these data and to obtain from them information which will be of use in refinements pile calculations. In cases, e.g. transport cross-sections, where experimental data do not suffice, the theory developed pertaining to the continuum model of the nucleus has been depended upon. One of the fundamental requirements of this model is that the spacings of the energy levels in the compound nucleus are small compared to their widths and that consequently many levels are excited by the incoming particles. As a result there are many more modes of decay and the continuum model is an average over these levels.

Technical report covering the technology of hot-pressed beryllium production and its rapid advancement toward the end of 1949. Part I is devoted to corrosion studies made on hot-pressed and vacuum cast extruded metal which was considered representative of production. Part II is concerned with the results of tests made on special cast and hot-pressed beryllium which contained added impurities. [From Introduction]

An investigation has been made in the Langley 9- by 12-inch supersonic blowdown tunnel to determine the effects of external-store location on the lift, drag, and pitching-moment characteristics of a 45 degree sweptback wing at Mach numbers of 1.41, 1.62, and 1.96. The spanwise, chordwise, and vertical location of a Douglas-Aircraft Company, Inc., store of fineness ratio 8.58 was systematically varied over the outer 60 percent of the wing semispan. A brief investigation of strut sweep angle was also made. The test Reynolds number based on the wing mean aerodynamic chord ranged from 1.3 x 10(exp 6) to 1.5 x 10(exp 6).

Abstract: "The protection of thorium in hot water was studied. Copper electrocladding on thorium offers promising protection against hot water. The corrosion of thorium in 95 C water was reduced appreciably by a thorium phosphate film. The results of this abbreviated investigation offer a basis for the development of a method of protecting thorium at elevated temperatures in corrosive media."

Report presenting a small-scale transonic investigation of a semispan wing sweptback 45 degrees and of aspect ratio 4 with combinations of nose-flap deflections and wing twist in the high-speed 7- by 10-foot tunnel over a range of Mach numbers. Lift, drag, and pitching-moment data were obtained for several different configurations.

Report detailing the refractive index of solutions of uranyl nitrate, nitric acid and aluminum nitrate. This report builds upon preliminary data and a brief discussion that from a previous report. This report covers more accurate and detailed data that had be accumulated following the initial report.

From introduction: "The study's objectives were to determine the approximate rate of general corrosion so as to reveal; any abnormal corrosion occurring during processing operations; to determine the suitability of a large variety of alloys and plastics as materials of construction; and to ascertain process conditions which would minimize corrosion."

Among the safety considerations for the Purex plant is the question of flammability limits for the diluent-air system. The present note attempts to delineate the temperature regions of concern by utilizing hydrocarbon flammability data available together with information on the vapor pressures of the systems.

A combination sliding-ring and pressure-balancing seal capable of transferring pressurize air from stationary to rotating parts was developed and experimentally investigated at sliding velocities and cooling-air pressures up to 10,000 feet per minute and 38.3 pounds per square inch absolute, respectively. Leakage of cooling air was completely eliminated with an expenditure of balance air less than one-fourth the leakage loss of air from labyrinth seals under the same conditions. Additional cooling of the carbon-base seal rings was required, and the maximum wear rate on the rings was about 0.0005 inch per hour.

"An experimental investigation of combustor total-pressure loss was undertaken to confirm previous theoretical analyses of effects of geometric and flow variables and of heat addition. The results indicate that a reasonable estimate of cold-flow total-pressure-loss coefficient may be obtained from the theoretical analyses. Calculated total-pressure loss due to heat addition agreed with experimental data only when there was no flame ejection from the liner at the upstream air-entry holes" (p. 1).

Report presenting flutter characteristics at transonic speeds of a model of a fighter-type-airplane wing over a range of Mach numbers. The results indicated an abrupt increase in flutter speed ratio near a Mach number of 1.0, with only slight increases noted as it was increased to 1.4. Results regarding the effect of flutter-boundary shape are provided.

The HRT refrigeration system was designed to use Freon-11 (CCI3F) as the refrigerant material in the secondary loop. A Van de Graaff irradiation of this material indicated that serious corrosion problems were probable if Freon were used in the proposed metal system. A survey was made of candidate refrigerants, and Amsco 125-82 and triethyl phosphate were selected for irradiation and physical-property determinations.

Report presenting an investigation of a transonic turbine with a 0.6 hub-tip radius ratio in order to determine the effect of stator and rotor secondary flows on turbine performance. Results regarding the overall performance, stator exit surveys, and rotor exit surveys are provided.

Characteristic velocities of six single-element injectors that separately varied propellant spreading and mixing were measured over a range of oxidant-fuel weight ratios of 2 to 7. Hydrogen inlet temperature was -320 degrees F. Injectors that both mixed and spread the propellants had the highest characteristic-velocity efficiency. Spreading of either propellant produced about the same increment efficiency. The increase in efficiency due to mixing was relatively small. With similar injectors, oxygen-hydrogen required about 0.2 to 0.5 of the combustor volume of oxygen-heptane for the same efficiency.

Report presenting eight thin magnesium fins, seven with the leading edges swept back 17 degrees and one with the leading edge swept back 45 degrees, in the preflight high-temperature jet. The investigation was made to determine the effectiveness of various protective coverings designed to alleviate aerodynamic-heating effects and intended for application on the first stage of rocket-propelled multistage hypersonic models.