Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.

Report presenting testing of a full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Static and dynamic longitudinal stability and control derivatives were determined at low angles of attack and for a range of Mach numbers.

Report presenting flight testing and analog-computer studies using flight-test results of a swept-wing jet fighter in the landing condition to determine the factors that influence a pilot to select the minimum approach speed for carrier-type landings. Many factors that influenced the pilot occurred in approximately the same speed range, and the quantitative determination of the influence of each factor was not possible. Results regarding measurement of airplane and engine characteristics, field-carrier landings, and analog simulation of airplane and hypothetical autopilot in high-dip maneuver at constant thrust are provided.

The variation of breakaway time, time for scale color change, and metal growth with temperature for arcand graphite melted Zr in oxygen are presented. (For preceding period see AECU-3529.) (auth)

"Rocket-boosted free-flight tests of two models of an airplane configuration having a 45 degree swept wing and a low horizontal-tail position have provided lateral stability derivatives and control effectiveness data for a Mach number range from 0.8 to 1.7. The experimental lateral stability derivatives presented are corrected to rigid conditions and compared with theoretically calculated rigid derivatives. The results are presented without detailed analysis" (p. 1).

A second thermoelectric generator consisting of unitized rings of thermopiles was designed and constructed. Three and four rings were asserabled into generators and tested. A maximum efficiency of 0.67% was obtained. At a DELTA T of 400 deg C, an efficienty of 0.56% was obtained; the theoretical maximum for the materials used is 0.83%. (auth)

A summary of the research work done over a 9 1/2 year period and lists of reports and publications are given. The research program involved the development and application of ion exchange, solvent extraction and other methods to the recovery of uranium and other values from ores and leach solutions and exploratory studies on processes for manufacture of reactor-grade UF/sub 4/ at ore-processing mills. (auth)

Progress is reported in studies on the metabolism, radiation dose, radiation effects, and toxic effects of prolonged expesure of dogs following injection of various doses 8/, Th/sup 228, and Sr/sup 90/ An imporved live dog gamma counter is described. (For preceding period see AECU 3522.) (C.H.)

"The linearized theory of Tulin and Burkart for two-dimensional supercavitating hydrofoils operating at zero cavitation number is applied to the derivation of two new low-drag configurations. These sections were derived by assuming additional terms in the vorticity distribution of the equivalent airfoil; in particular, three and five terms were considered. A simplified calculation of the location of the cavity boundary streamline for arbitrary configurations is also presented" (p. 1).

Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.

Topics discussed include procedures for the determination of Po in urine, feces, and blood; the determination of Be in biological materials; application of statistical methods to bio-assay; techniques for low-level alpha counting and pulse-height analysis; the toxicology of plutonium; the metabolism and toxic effects of fission products; methods for the radiometric determination of I/sup 131/ and Sr/sup 90/ in urine; procedures for the radiochemical analysis of Sr and Ba in human urine; and the design and performance of a wholebody gamma counter. (See also NLCO-595.) (C.H.)

Six types of instruments are being considered for the metering of flow and/or density in high temperature (300 deg C) and pressure (2000 psi) slurry flow systems. Three of these meters yield readings that depend only on the flow rate or the density, one (the Double Rotameter) yields two readings from which both the flow and the density may be determined while another (the venturi) yields a reading that depends on both the flow rate and the density and thus may be either a density-meter or a flowmeter depending on which variable is the unknown. The remaining instrument (the ultrasonic meter) may yield a signal dependent solely on the flowrate or the density depending on the physical setup. This memo briefly describes these instruments, listing their particular advantages, the difficulties that may arise in their use and the state of development of each. (auth)

This report addresses the constant-pressure leak rate gage.

Memorandum presenting tests conducted to determine the flight characteristics of an F-86F airplane equipped with an area-suction-type boundary-layer control installation on the trailing-edge flaps. Measurements were made of the lift, drag, and engine bleed-air requirements. Results regarding the aerodynamic characteristics as well as some miscellaneous characteristics are provided.

Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.

Report presenting an investigation of resistance screens for the purpose of obtaining uniform flow in ducts. The new screen designs consisted of several different screen shapes with the elements set at oblique angles (swept) to the flow. Results regarding a rectangular channel and diffuser investigation are provided.

Property changes in polycrystalline graphite resulting from reactor irradiations at temperatures up to 185 deg C and over a range of exposures up to 1135 Mwd/ CT have been determined. Changes in stored energy, thermal conductivity, sample length, and C/sub O/ interlayer crystallite spacing are markedly decreased as exposure temperature is increased. Electrical resistivity changes are also less at higher exposure temperatures, but this property change does not depend as strongly on temperature as the others. Isothermal annealing studies of C/sub O/ changes were conducted on a number of irradiated samples. The data were analyzed assuming a large number of processes distributed in activation energy. The results are summarized in activation energy spectra in which the distribution of C/sub O/ damage is given as a function of the activation energy required for annealing. It is found that not only does a higher exposure temperature decrease the total amount of property change, but also the distributlon of damage accumulated is considerably different. Results are discussed in terms of the radiation damage model suggested by Hennig and Hove. This model is compatible with the experimental results presented. (auth)

Review of ThO/sub 2/ caking and sphere forming experiences in the 200 and 100 gpm loops shows that cakes and spheres always formed in the first 100 hours of the run or did not form at all, suggesting that processes in addition to oxide particle degradation were present. Many ThO/sub 2/ circulation tests in which no major difficulties were experienced suggest that preparation of oxides suitable for reactor use may have been accomplished, at least insofar as the caking problem is concerned. Further research is required to distinguish between oxide preparations. Evaluation of ThO/sub 2/ batches by cake resuspension index'' studies are described. A qualitative indication of the caking tendency of various batches of ThO/sub 2/ is given. Observations of ThO/sub 2/ sphere growth in stirred systems at atmospheric pressure indicate that added electrolytes have a strong influence. The results of ThO/sub 2/ cake disintegration tests are reviewed. A cake disintegration method has been used successfully twice to remove hard cake from inaccessible points in loops. The proposed program for caking studies in the 30 gpm loop, which is under construction, is outlined. The potential usefulness of several avenues for investigation of ThO/sub 2/ surface chemistry is indicated and the …

Report presenting the lift and drag characteristics of a 60-degree delta-wing interceptor airplane with fuselage extension and indentation at a range of Mach numbers and altitudes. A comparison with a prototype airplane and a comparison of the flight results with the model tests are provided.

Report presenting the lift and drag characteristics of a 60 degree delta-wing interceptor airplane with a fuselage extension and indentation. The data was obtained over a range of Mach numbers and altitudes. Results regarding a comparison with a prototype airplane with similar wings and a comparison of the flight tests with model tests are provided.

Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.

Report presenting a wing-root inlet configuration with varying inlet components that were tested in the supersonic pressure tunnel at several Mach numbers, angles of attack, and sideslip angles. The intent was to determine the effects on inlet performance and engine-face total-pressure distributions of variations in these variables. Some inlet-lip stagger was found to improve pressure recoveries at high angles of attack with little to not compromise at an angle of attack of 0.

Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compared to a previous study involving a model with a thicker cantilever wing.

Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist. Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.