General account with outline of route and life zones, and lists of mammals and birds.

This report describes the redesigned variable-density wind tunnel of the National Advisory Committee for Aeronautics; it supersedes a previous report that described the original tunnel. The operation of the balance and the method of testing are explained and the method of correcting and presenting airfoil data is described. A summary of the formulas for predicting the characteristics of finite wings from the airfoil section data as they are usually presented is also given.

From Summary: "The equations relating the wing and tail loads are derived for a unit elevator displacement. These equations are then converted into a nondimensional form and charts are given by which the wing- and tail-load-increment variation may be determined under dynamic conditions for any type of elevator motion and for various degrees of airplane stability. In order to illustrate the use of the charts, several examples are included in which the wing and tail loads are evaluated for a number of types of elevator motion. Methods are given for determining the necessary derivatives from results of wind-tunnel tests when such tests are available."

Technical report describing that the use of controlled amounts of carbonate, acting both as complexing agent buffer led to a fairly satisfactory procedure for the determination of Th in Th-U alloys, using cupferron. The alloy, dissolved in NHO2, in the presence of HF, is treated with H2SO4 and the mixture is evaporated in SO2 fumes. The solution is diluted and (NH4)2CO2 is added. Th is precipitated from this solution with cupferron. The precipitate is weighed as ThO2 after ignition. An accuracy of 6% was obtained. A method was developed specifically for the determination of Th in U-Th alloys containing 1 to 10% Th. An ion exchange resin in column is used to separate Th from U, with NH2OH-HCl as complexing agent. The Th is then precipitated, ignited, and weighed in the conventional manner.

From Summary: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the operational characteristics of a 3000-pound-thrust axial-flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Operational characteristics investigated include engine operating range, acceleration, deceleration, starting, altitude and flight-Mach-number compensation of the fuel-control system, and operation of the lubrication system at high and low ambient-air temperatures."

"Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configuration were simulated" (p. 1).

Discussing the Majuba Hill mine, located 20 miles northwest of Imlay, Nevada, and consisting of approximately 4000 feet of workings on three levels.

Two low-acceleration transonic-flutter vehicles were launched and flown. The first carried two test wings, one of which fluttered at M = 0.92 at a frequency of 61.4 cycles per second. The reference flutter speed determined from two-dimensional theory for an unswept wing in incompressible flow is conservative when compared to the experimental flutter speed. The second vehicle carried two test wings, one of which failed at M = 0.71 because of low-frequency divergent oscillation. Since this failure was not caused by conventional flexure-torsion flutter, no comparison with a reference flutter speed can be made.

Summary: "This report investigates photographic methods of measuring beta radiation and includes a study of temperature effects on these measurements. Experimental data are submitted to show that an increase in film temperature before and during beta irradiation causes a definite increase in density for the same dosage. Recommendations drawn from experience gained in the experimental works are offered."

"Theoretically derived charts showing the profile-drag-thrust ratio are presented for helicopter rotors operating in forward flight and having hinged rectangular blades with a linear twist of 0 degree, 8 degrees, and 16 degrees. The charts, showing the profile-drag characteristics of the rotor for various combinations of pitch angle, ratio of thrust coefficient to solidity, and a parameter representing shaft power input, are presented for tip-speed ratios ranging from 0.05 to 0.50. Also presented in chart form are the ratio of thrust coefficient to solidity as a function of angles of attack, as a function of inflow ratio and collective pitch, and as a function of power and thrust coefficients" (p. 1).

Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible to the pilots.

Report presenting results of a flight investigation of a radar fire-control system installed in a fighter airplane. Some of the factors included in the radar evaluation are "noise" of the steering dot, lack of target-attitude information, and sensitivity and linearity of the display.

Report presenting an investigation in the stability tunnel to determine the combined effect of wing and wing-body interference on the contribution of an x-tail configuration to the low-speed rolling-stability derivatives of an airplane model with an unswept midwing and to indicate the change due to roll in the local flow angularity at a number of stations across the tail surfaces for one-half of the x-tail. Results regarding the static longitudinal characteristics, steady-roll characteristics, and angularity measurements are provided.

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the chordwise and spanwise load distribution on a thin 60 degree delta-wing-fuselage model equipped with double slotted and extended double slotted flaps. The effects of a canard on the loads of the wing with the extended double slotted flaps are also determined.

A summary is given of the background and present status of the pure-planing theory for rectangular flat plates and v-bottom surfaces. The equations reviewed are compared with experiment. In order to extend the range of available planing data, the principal planing characteristics for models having sharp bottom surfaces having constant angles of dead rise of 20 degrees and 40 degrees. Planing data were also obtained for flat-plate surfaces with very slightly rounded chines for which decreased lift and drag coefficients are obtained.

The purpose of the test was to determine if failed blanket elements exist in other regions of the core beside F-2. FEDAL sampling ports that have indicted the greatest deviation as determined in a statistical analysis performed on a number of traverses in the FEDAL system will be tested. Data obtained from the start up runs of the FEDAL sample port Nos. 11, 31, 36 and 37 of Monitor 2 and port Nos. 14, 46, 11, 49 and 7 of Monitor 1 gave no indications of a blanket element failure. At each power increase, the radiation increase was normal with no signs of bursts or peaks of radiation which would indication the failure of a blanket fuel element.

This review lists some of the salient features of semiconductor particle counters and cannot claim to contain an exhaustive listing of all the work in the field. Performance results on the surface-barrier counters as developed at California Institute of Technology are included as typical for this type of counter, though comparable results have been obtained elsewhere.

The PWR Plant was operated at approximately 60 MW net electrical output for a total of 1000 EFPH from February 3, 1959 to March 28, 1959. During this period, while performing DL-S-225, there were two planned shutdowns, no safety shutdowns or safety insertions and one flux title. The performance of the plant was satisfactory during the period of the test.

The utilization of gloves wherein heavy element additives have been included is a significant means of reducing exposure to hands and, consequently, increasing allowable working time in operations which require direct contact with low energy isotopes - such as plutonium. The number of such gloves available has been limited considerably by the feasibility of fabrication and the practicality of application. The following study was made on two basic gloves - the first, a heavy zinc-neoprene coated glove and the second, a lead loaded neoprene glove available in two thicknesses. Included in the study was a standard 30 gauge neoprene glove.

Report of the annual conference on weights and measures, hosted by the U.S. National Bureau of Standards in Washington D.C. It includes conference proceedings, a list of attendees, information about committees and officers, and other reports or commentaries discussed at the meetings.

Report providing an alphabetical listing of the periodicals, both American and foreign, that are currently being received in the Washington (D.C.) Library of the National Bureau of Standards. Approximately 2,000 titles are cited, together with call numbers indicating the location of each in the NBS Washington Library. Although this information was compiled primarily for the use of the Bureau's scientific staff, it is also of value to libraries, scientific and technical organizations, and research workers.