"An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through electrically heated Inconel tubes having various degrees of square-thread-type roughness, an inside diameter of 1/2 inch, and a length of 24 inches were obtained for tubes having conventional roughness ratios (height of thread/radius of tube) of 0 (smooth tube), 0.016, 0.025, and 0.037 over ranges of bulk Reynolds numbers up to 350,000, average inside-tube-wall temperatures up to 1950deg R, and heat-flux densities up to 115,000 Btu per hour per square foot" (p. 1).

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."

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.

Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.

A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.

The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.

Report presenting an investigation at low speed in the Langley full-scale tunnel of the downwash, sidewash, and wake behind a large-scale 60 degree triangular wing with 10-percent-thick biconvex airfoil sections. Results regarding the air-stream surveys for three different configurations and stability and trim are provided.

Memorandum presenting an investigation to determine the practicability of using blade boundary-layer control in order to obtain high turning angles in a stator-blade row. The overall performance of the stage was obtained for a range of weight flows at each of three tip speeds with and without hub section. Results regarding slot configuration, overall performance, and stator-blade wakes are provided.

Report discussing an investigation into the effects of camber and leading-edge-flap deflection on the pressure pulsations on thin rigid airfoils at a range of Mach numbers. The ideal camber or flap deflection was found to be dependent on Mach number and normal-force coefficient. The results of this testing, which used a 64A006 airfoil, was compared to previous testing using a 65A006 airfoil.

Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of external store location on the lift, drag, and pitching-moment characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96. Brief comparative tests were also made to determine the effect of changing the sweep of the strut attaching the store to the wing and of changing the chordwise location of the swept strut.

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."

Report presenting a wind-tunnel investigation to determine the low-speed static and rotary stability derivatives of a model of the Douglas D-558-II airplane in the landing configuration. Results regarding the static longitudinal characteristics, static lateral characteristics, characteristics in rolling flow, and characteristics in yawing flow are provided.

From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."

Report presenting an evaluation of the relative importance of heat-transfer modes in an experimental afterburner. The convective heat-transfer coefficients near the combustion-chamber outlet were determined and the effects of three radial distributions of afterburner fuel across the turbine-outlet annulus on the convective heat-transfer coefficient were examined.

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.

Report presenting the use of the matrix-integration method for calculating static aeroelastic phenomena on a wing with concentrated aerodynamic forces at the tip due to tip tanks or boom-mounted lifting surfaces. The results indicate that the presence of a tip tank on an unswept wing tends to deteriorate its static aeroelastic characteristics and that a lift surface geared to the aileron and mounted on a boom ahead of the tip may improve the static aeroelastic characteristics to warrant consideration of a vane as a device for relieving adverse aeroelastic effects.

A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Necessity that bedding manufactured in Texas for sale outside the State comply with bedding stamp requirements of the Texas Bedding Act.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Necessity that an employer allow employees time off to vote when the employees have sufficient time to vote outside working hours.

An analysis is made of the heat produced by the absorption of gamma rays in a sample placed into a reactor. It is clearly shown that enormous local (space) variations in gamma flux exist in current reactors. An application to the Hanford reactors is treated in some detail. Although the estimates obtained may be good to but a factor of two, it is clearly shown that in most cases the major portion of the heating is due to (n, {gamma}) reactions within the sample itself, and in some cases to the gamma rays generated in liners and cans, and not from the gamma rays generated in fission, nor from the moderator. Some implications of these results are discussed, among the most important being their application to radiation chemistry in reactors. Several mathematical results for absorption and generation of gamma rays in various bodies which should be useful in estimating dosage rates for samples irradiated in reactors are given (Appendix II). A method for making the calculations for an arbitrary absorption law are given (Appendix III). This method may be used with the true absorption law for gamma rays or even for the calculation of the absorption of the energy of …

From introduction: The Monument No. 2 mine is in the Navajo Indian Reservation, Apache County, Arizona, about 20 miles southwest from the San Juan River at Mexican Hat, Utah, and 26 miles southwest from Mexican Water, Arizona. The property has been operated, since its discovery, by Vanadium Corporation of America, which holds a 10-year mining lease, granted through the Interior Department, to 43 acres of ground. History of the discovery of the deposit is vague, but reportedly it was first seen around 1942 by a Navajo who mentioned the occurrence to Harry Goulding, Indian trader, who in turn advised D. W. Viles of Vanadium Corporation of America. Minor portions of the deposit are held by Cato Sells and Harvey Black, Navajos, under mining permits issued by the Navajo Tribal Council. The Sells acreage is being operated by Climax Uranium Corporation.

A vacuum pump based on the properties of a magnetically collimated electric discharge is described. It has a speed in the range 3000 to 7000 liters a second and a base pressure in the order of 10{sup-6}mm.

This report discusses the high-velocity collisions of two identical solid plates driven by high explosives. The collision data employs dural, mild steel, brass and lead, as well as experimenting with jetless and jet-forming collisions.

The question of maximum permissible levels of fission products or corrosion products in the pile effluent water which you raised is not a simple problem that can be completely answered by a list of maximum permissible levels. This water is a complex mixture of various isotopes each of which contributes to the total hazard according to the amount present, its particular metabolic features, and its mode of radioactive decay. Unfortunately, also, application of maximum permissible limits determined for consumption by humans may give only a part of the picture since it is necessary to consider also the effect on the ecology of the Columbia River and the ultimate effect on the aquatic life. With these considerations, we can make estimates of some limits which may be applied in design of new systems with, however, the reservation that practical application may depend on the mixture of isotopes actually encountered in operation. This document provides a discussion of maximum permissible levels of radioactive effluents and corrosion products in the reactor cooling water. 5 tabs.