In order to obtain a correlation of drag data from wind-tunnel and flight tests at high Mach numbers, a typical pursuit airplane, with the propeller removed, was tested in flight at Mach numbers up to 0.755, and the results were compared with wind-tunnel tests of a 1/3-scale model of the airplane. The tests results show that the drag characteristics of the test airplane can be predicted with satisfactory accuracy from tests in the Ames 16-foot high-speed wind tunnel of the Ames Aeronautical Laboratory at both high and low Mach numbers. It is considered that this result is not unique with the airplane.

Abstract. The effect of various inhibitors on the production of CrIII in W waters containing chromatic has been studies at a variety of pH's in the CP-3 pile. The addition of 2 ppm NaClO3 appears to have little effect a a pH of 5.3, but 2 ppm NaClO3 cr 0.15 ppm of Cl2 (in the form of NaOCl) somewhat decreases the amount of chromatic reduced at a pH of 7.1. The inhibition is not great enough, however, to reduce the amount of CrIII formed to the maximum concentration permissible at W (0.02 ppm). The addition of 3 ppm (NH4)2S2O3 as an inhibiter will permit W water to be used a a Ph of 7.0, but not at a pH of 6.5 as far as chromate reduction is concerned. The concentration of CrIII would be 0.01 ppm and 0.05 ppm, respectively, after one passage through the pile. Previous conclusion as to the effects of temperature, pH, intensity and the addition of ammonium persulfate, which had been reached from experiments with simulation W water, have been checked by studies with solutions made from water chipped directly from Hanford. All of the effects noted were found to be similar to those already reported, …

Abstract. Wigner effects on aluminum, beryllium, and tuballoy have been studied by the electrical resistance method. Samples were exposed during an interval which would have produced an increase of approximately 22% in resistance of AGOT-K graphite. The resistance of tuballoy increased approximately 1%. It is shown that the increase can be accounted for by the amount of fission product impurity formed during the exposure. Neither aluminum nor beryllium showed any change. In the case of Be, the Wigner effect may be obscured, to some extent, by the approximately .2 - .3 atom % of impurity present in the samples. Based on the increase occurring in ADOT-K graphite, a change of approximately .2 - .5 x10-6 ohm-om might be expected in the case of Be. The accuracy of the method was sufficiently great to detect a change of this magnitude. Other experiments with Be will be undertaken when purer samples are available. Meanwhile, some samples of the present type ae being subjected to further irradiation.

From Summary: "Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemeters and a Doppler velocimeter radar unit."

Abstract: "A method for the potentiometric titration of uranium with ferric sulfate is described. This method provides a rapid and accurate way of determining the element in solutions free from interfering ions. Application of the method to analysis of pure uranium compounds and to uranium recovered from contaminated solutions by suitable procedures is briefly discussed."

A heat-transfer investigation was conducted with air in an electrically heated platinum tube with long-approach entrance, inside diameter of 0.525 inch, and effective heat-transfer length of 24 inches over ranges of Reynolds number up to 320,000, average inside-tube-wall temperature up to 3053 degrees R, and inlet-air temperature up to 1165 degrees R. Correlation of data by the conventional Nusselt relation resulted in separation of data with tube-wall temperature. Good correlation was obtained, however, by use of a modified Reynolds number.

From Introduction: "The purpose of this paper is to provide further information on the effects of Reynolds number on the aerodynamic characteristics of the wing of reference 1 as well as to provide load distributions for the wing at Mach numbers of 1.6 and 1.9."

Memorandum presenting some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach number of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. The plan forms, airfoil sections, and thickness ratios of the wings tested are provided.

From Introduction: "This paper presents some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach numbers of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. Data on lifting wings in the Mach number range above 2.5 are not plentiful and most of the available data may be found in NACA RM L51D17, NACA RM L51D30, NACA RM L52D15a, NACA RM L52K19, NACA RM L53D03, and NACA RM L53D30a."

Report presenting an investigation in the Langley 300 mph tunnel to determine the low-speed static stability and control characteristics of a model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4 wing. Tests were also made to determine optimum flap deflection for a slotted flap. Results regarding longitudinal stability and control, high lift devices, lateral and directional stability, and lateral and directional control are provided.

Report presenting testing of a 20 degree semiangle conical-inlet ramjet engine with a design Mach number of 2.13 in free supersonic jets to determine the inlet and combustion performance over a fuel-air ratio and Mach number range. Results regarding preflight and flight testing are provided.

From Summary: "An investigation has been conducted in the Langley 8-foot transonic tunnel to determine the effects of several fuselage modifications on the transonic drag-rise characteristics of a 1/20-scale model of the Convair F-102 airplane. Tests covered an angle-of-attack range from 0 degrees to about 10 degrees and a Mach number range from 0.60 to 1.14."

Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distribution at six spanwise stations on a 45 degree sweptback, untapered vertical tail in sideslip. The presence of the horizontal tail slightly increased the value of section normal-force coefficients on the vertical tail but did not materially alter the nature of the load distribution.

From Summary: "Some of the methods of predicting rotor stability derivatives have been reviewed. The methods by which these rotor derivatives are employed to estimate helicopter stability characteristics have been summarized. It is concluded that, although these methods are not always feasible for predicting absolute values of the stability of the helicopter, the effects on stability of changes in individual derivatives can generlaly be estimated satisfactorily."

Memorandum presenting the carpet-plotting technique as a more useful and concise method of summarizing the 65-series compressor-blade cascade data. Four different carpet plots are presented. A sample use of the carpet plots is also provided.

From Summary: "The paths of cloud droplets into two engine inlets have been calculated for a wide range of meteorological and flight conditions. The amount of water in droplet form ingested by the inlets and the amount and distribution of water impinging on the inlet walls are obtained from these droplet-trajectory calculations. In both types of inlet, a prolate ellipsoid of revolution represents either part or all of the forebody at the center of an annular inlet to an engine. The configurations can also represent a fuselage of an airplane with side ram-scoop inlets. The studies were made at an angle of attack of 0 degree. The principal difference between the two inlets studied is that the inlet-air velocity of one is 0.7 that of the other. The studies of the two velocity ratios lead to some important general concepts of water ingestion in inlets."

Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.

Report presenting an investigation of an airplane model conducted to determine the effect of area-suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. Results regarding the effect of trailing-edge flaps on the aerodynamic characteristics of the model with horizontal tail off, effect of wing modifications on the high-lift characteristics of the model with the horizontal tail off, aerodynamic characteristics of the model with the horizontal tail installed, and area-suction requirements are provided.

Progress report of the Oak Ridge National Laboratory Metallurgy Division providing updates on various projects, experiments, and other work. This report includes a summary of scholarly output and summaries of general corrosion, dynamic corrosion, mechanical properties, nondestructive testing, welding and brazing, fabrication, physical chemistry of corrosion, HRP metallurgy, the package power reactor program, APPR absorber, metallurgical materials and processing, metallography, ceramics, fundamental physico-metallurgical research.

The accuracy and durability of two means for measuring the metal temperature of gas-turbine blades were investigated experimentally in a turbojet engine. Cemented thermocouples that could be placed in walls as thin 0.010 inch and commercial temperature-indicating paints were evaluated at turbine-inlet temperatures up to about 1650 degrees F and for centrifugal forces equivalent to about 42,000 times gravity. The cemented thermocouples operated satisfactorily. The temperature-indicating paints were neither as accurate nor as durable as the cemented thermocouples.

Report discussing a study that investigates the use of small amounts of tracer elements placed in the fuel alloy of subassemblies in order to locate fuel-element failure. Details of experimental methods and materials are included as well as data that leads to the suggestion of further investigation.

The first series tests in the KER-REP-1 loop proved that a fisssion product contaminated loop could be decontaminated to a safe level for contact maintenance. The second series of tests ere scheduled for a more thorough evaluation of these processes includes specific decontamination factors, process corrosion rates, loop activity reduction factors (loop decontamination factors), and any preferential decontamination which may be present.

Report documenting ongoing research and development carried out by the Instrumentation and Controls Division of the Oak Ridge National Laboratory.

When following the performance of automatic and semi-automatic equipment that is left unattended for extended periods of time, it is often desirable to be able to check this equipment by remote means. A convenient vehicle for such a check is the telephone since nearly all locations have or can have a telephone extension installed. The check of the equipment may be made as simple or extensive as desired, with the outcome of the check represented by a relay condition, for example. The condition of the relay is then transmitted to the interrogator over the telephone line by means of the presence or absence of a tone.