Introduction: This document describes the results of a six-week conceptual design study of an organic moderated and cooled reactor (OMCR) power plant adapted to a Class T-7 tanker.

From Abstract: "Automatic computation of these general formulas from raw data and procedures for their adaption to a number of specific analyses are described."

"The phase and amplitude functions describing the betatron oscillations in the synchrotron are calculated using the revised parameters of the Cambridge Electron Accelerator. The results are given numerically and plotted in a graph for one machine period."

Report presenting some work done to meet the requirements of missile control designers for more powerful controls and for lower hinge moments. Some testing regarding all-movable wings and reducing hinge moments is described.

Memorandum presenting an investigation of the possibility of correlating airfoil section data with measured pressure distributions over a 45 degree sweptback wing in the Mach number range from 0.50 to 0.95 at a free-stream Reynolds number of approximately 2 million. The wing had an aspect ratio of 5.5, a taper ratio of 0.53, NACA 64A010 sections normal to the quarter-chord line, and was mounted on a slender body of revolution. Results regarding correlation of chordwise pressure distributions, correlation of magnitudes of section loads, and wing-body characteristics are provided.

Report presenting longitudinal and lateral-directional frequency responses determined from transient flight data excited by control pulses for a large flexible swept-wing airplane over a wide range of flight conditions. The effects of structural modes on the frequency response at various locations on the airplane are shown. Results regarding the low-frequency response, longitudinal transfer-function coefficients, lateral response, lateral-directional transfer-function coefficients, experimental technique, and high-frequency responses are provided.

Report presenting an investigation of the effects of streamwise gaps between wing and body on the lift and pitching moments of a moderately slender wing-body combination at Mach number 1.4 and compared with available theoretical results. The investigation included tests in which the angle of attack is varied with the all-movable wing at zero deflection and also tests at which the angle of wing deflection is varied with the body at zero angle of attack.

Report presenting an investigation at Mach number 1.62 of a series of triangular wing and body combinations to determine the interference lift, drag, and pitching moment. Testing was conducted on seven flat-plate triangular wings of varying scale, four with a half-apex angle of 30 degrees and three with a half-apex angle of 45 degrees. Results regarding wing alone, wing in the presence of the body, basic quantities for interference evaluation, interference quantities, and contributions of both types of quantities are provided.

"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).

Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.

A transistorized binary counter circuit is described that operates over a temperature range of -65 degree F to +165 degree F. the supply voltage is 28 + 4 volts and the maximum trigger repetition rate is 5 kilocycles. the binary circuit is pre-settable and resettable by means of a switching arrangement that can be mechanized. Texas Instrument type 904 silicon transistors whose large signal current gain is 2.8 or greater at a -65 degree F can be used in this circuit.

Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.

Report regarding the mathematical analysis of the exponential pile experiment using highly absorbent slugs and assuming the emitting of fast neutrons. Related theory and equations are discussed.

During the canning of slugs for Production Test 313-105-3-M, a high number of rejects were caused by gas voids in the A1-S1 bonding layer. Since the heat treatment of the slugs in a molten salt bath resulted in a chemically altered surface, an investigation was made to determine the volume of gas evolved from salt-bath heat-treated slugs as compared to other types of slugs. This test was designed as a preliminary test to determine if there were a significant differences.

Photogeologic map of the Orange Cliffs-3 quadrangle, Wayne County, Utah

From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."

From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat-exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."

Map of the area surrounding the census-designated place of Beclabito, San Juan County, New Mexico showing mine locations and mineralized rock exposures by geologic period, along with the location of triangulation stations with their elevation.

Preliminary recommendations are presented for drilling the area on a 1,000-foot grid to provide final elevation of the East Carrizo mining district.

Report presents the results of an investigation conducted to determine the effectiveness of liquid-cooling films on the inner surfaces of tubes containing flowing hot air. Experiments were made in 2- and 4-inch-diameter straight metal tubes with air flows at temperatures from 600 degrees to 2000 degrees F. and diameter Reynolds numbers from 2.2 to 14 x 10(5). The film coolant, water, was injected around the circumference at a single axial position on the tubes at flow rates from 0.02 to .24 pound per second per foot of tube circumference (0.8 to 12 percent of the air flow). Liquid-coolant films were established and maintained around and along the tube wall in concurrent flow with the hot air. The results indicated that, in order to film cool a given surface area with as little coolant flow as possible, it may be necessary to limit the flow of coolant introduced at a single axial position and to introduce it at several axial positions. The flow rate of inert coolant required to maintain liquid-film cooling over a given area of tube surface can be estimated when the gas-flow conditions are known by means of a generalized plot of the film-cooling data.

Map showing uncontrolled structure contours of the Beclabito Dome Area, Shiprock District, Arizona-New Mexico. The Salt Wash-Bluff contact was spotted on aerial photographs as a basis for the construction of the uncontrolled structure contour map

Report presenting preliminary results of one phase of a control-motion study program using data obtained from 276 maneuvers performed using a McDonnell F2H-2 jet fighter airplane during normal squadron operational training. Results regarding classification of maneuvers, airspeed, load factors, sideslip angle, and maximum pitching-, rolling-, and yawing-angular-acceleration variations with indicated airspeed are provided.