Report discussing a possible solution for providing a remotely operated way of handling samples at an irradiation facility. Explanation of operating requirements, equipment, and a possible layout is included.

Report discussing a test aimed at determining if high velocity water could cause severe pitting in 72-S aluminum. This test was designed after an increase in the amount of pitting-caused water leaks in reactors.

Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.

Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and longitudinal characterisitcs with the flaps deflected are provided.

"Investigations in the Langley 20-foot free-spinning tunnel of models of five jettisonable nose sections have shown that the airplane nose sections are inherently unstable but can be stabilized by the addition of suitable fins. An empirical criterion has been developed which indicates the fin area required for stabilizing an airplane jettisonable nose section" (p. 1).

Report presenting an investigation of the low-speed lateral characteristics of a 47.5 degree sweptback-wing-fuselage combination with several flap and spoiler aileron arrangements. Results regarding aileron control characteristics, spoiler-control characteristics, and a comparison of the two are provided.

Report presenting a study of the storage properties of fuming nitric acids, with and without additives, at 170 degrees F in closed containers of aluminum bodies and steel caps. The effects on the storage properties indicated that the potassium fluoride dihydrate is most effective in reducing the rate of pressure rise and reducing corrosion on aluminum and stainless steel surfaces.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a spoiler-slot-deflector combination in producing rolling moments in the transonic speed range at angles of attack as high as 24 degrees over a range of Mach numbers. The wing had an aspect ratio of 4, a taper ratio of 0.6, an unswept quarter-chord line, and NACA 65A006 airfoil sections.

Report presenting an investigation to determine the performance of a conical-nose supersonic diffuser at angle of attack. The inlet had a pivoting cone which could be oriented to any of several angles independent of the angle of attack of the diffuser. Results regarding total-pressure recovery and mass-flow characteristics, cowl lip position, cone position relative to angle of attack, shadowgraphs, and contour maps are provided.

Report presenting a flight investigation to study in detail the response of an airplane structure during buffeting. Measurements of acceleration on selected points were made during buffeting for two different conditions of lift coefficient and Mach number and the time histories of acceleration were studied using electrical frequency-analysis techniques. Results regarding the ground response measurements, response to buffeting excitation, verification of the measured results, and the pilot's observation of the buffeting are provided.

As previously reported, zirconium undergoes large dimensional increases after scaling in air in a critical temperature range, 700 degree-1050 degree C. This finding was observed with specimens of a constant thickness (0;062 in.) To study the thickness effect, a number of specimens ranging in thickness from 0.020 to 0.200 in. were scaled in air at a temperature (900 degree C) where the growth is a maximum for a given time. Both cold rolled iodine sheet and forged iodide bar stock were used. to determine the effect of orientation, specimens from the forged bar were obtained such that the scaling surface was either parallel to or perpendicular to the long axis of the bar.

"Because previous work has indicated that jettisonable nose sections of airplanes may be inherently unstable, and thus may cause dangerous centripetal accelerations on a pilot after jettisoning during high-speed flight, an investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the behavior in descent of a model of the jettisonable nose section of the Douglas X-3 airplane. The effects of varying the center-of-gravity position, of attaching fins of various sizes, and of installing a stabilizing parachute were investigated. In the investigation the model descended with its front and trimmed 36 deg above the horizontal and rotated about a vertical wind axis while rolling about its longitudinal body axis" (p. 1).

The gust and draft velocities from records of NACA instruments installed in P-61c airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from July 12, to July 18, 1947 are presented.

Report presenting an investigation in the 8- by 6-foot supersonic tunnel at a range of free-stream Mach numbers at zero angle of attack to determine the effects of internal corner fillets on the pressure recovery characteristics of twin-scoop conical-type inlets utilizing boundary layer removal and mounted on the RM-10 body. Without boundary layer removal, the use of fillets resulted in substantial improvements in pressure recoveries and near critical mass flows up to a certain Mach number.

"Results are given of pressure-distribution measurements made over two different horizontal tail surfaces and the right wing cellule, including the slipstream area, of an observation-type biplane. Measurements were also taken of air speed, control-surface positions, control-stick forces, angular velocities, and accelerations during various abrupt maneuvers. These maneuvers consisted of push-downs and pull-ups from level flight, dive pull-outs, and aileron rolls with various thrust conditions" (p. 319).

"Free-flight tests in the transonic and supersonic speed ranges utilizing rocket-propelled models have been made on two pairs of 1/9-scale Convair YF-102 airplane wings with elevons to investigate the possibility of flutter . These wings had modified 60 deg delta plan forms with the trailing edge swept forward 5 deg. The aspect ratio of two exposed wing panels was 2.19 and the wings had NACA 0004-65 (modified) airfoil sections. The model wings and elevons were dynamic-scale models at sea level of the full-scale wings at 20,000 feet" (p. 1).

MTA quarterly progress report for June-August 1952

From abstract: Results of a reconnaissance geochemical survey of the Enid Quadrangle, Oklahoma are reported. Field and laboratory data are presented for 677 groundwater and 516 stream sediment samples. Statistical and areal distributions of uranium and possible uranium-related variables are displayed. A generalized geologic map of the survey area is provided, and pertinent geologic factors which may be of significance in evaluating the potential for uranium mineralization are briefly discussed.

Studies are being made on the effects of variation of aluminum content, heat treatment, surface preparation, and other metallurgical factors on the room temperature ductility of Al-- Fe alloys. It is estimated that approximately 65 percent of the proposed research has been completed over the first eight and one-half months of the contract period.

The purpose of the test was to fill the condensate storage tank and the Condensate System and obtain satisfactory preliminary operation. The components of the Condensate System performed adequately and satisfactorily with the exception of fill control valve (M9-VI). This valve (M9-VI) is not used in the current operation procedure.

The purpose of the test was to evaluate the operation of the Nuclear Instrumentation Power Range Amplifier during start up. While the station was operating at a gross load of 16.5 megawatts, a variation of 0, 8.5, 2.7 and 4.4 existed between the compensated ion chamber currents (CIC) and the test currents for channels A, B, C and D respectively. The off site modifications to channel C power range amplifier did not cause the ion chamber current and test current to be the same at 16.5 megawatts gross power. The modifications to channel C were made to correct for this deficiency.