From Summary: "The experimental and calculated aerodynamic characteristics of 22 tapered wings are compared, using tests made in the variable-density wind tunnel. The wings had aspect ratios from 6 to 12 and taper ratios from 1:6:1 and 5:1. The compared characteristics are the pitching moment, the aerodynamic-center position, the lift-curve slope, the maximum lift coefficient, and the curves of drag. The method of obtaining the calculated values is based on the use of wing theory and experimentally determined airfoil section data. In general, the experimental and calculated characteristics are in sufficiently good agreement that the method may be applied to many problems of airplane design."

The following report is a study of the separating qualities of a loop-type separator that can obtain separation with a smaller pressure drop.

"An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impossible to obtain satisfactory lateral-flight characteristics even with the increase in height of the vertical tail because of the negative effective dihedral, low directional stability, and large-adverse yawing moments of the ailerons" (p. 1).

Report presenting control requirements and parameters for a ram jet with a variable-area exhaust nozzle, which have been analyzed from calculated performance charts covering flight Mach numbers from 0.6 to 3.0 and altitudes from sea level to 30,000 feet. Requirements for maximum efficiency, safe and stable operation, maximum range of thrust at a given flight Mach number, and control of fuel flow are discussed and control parameters are selected.

Report presenting an experimental investigation to determine the effect on inlet performance of several boundary-layer scoops mounted inside a ramp-type inlet in the 8 by 6-foot supersonic wind tunnel over a range of Mach numbers. Results regarding typical variations of inlet-diffuser pressure recovery, peak recovery, inlet stability range, and effect of inlet sizing are provided.

The penetration rates of thorium metal by boiling nitric acid were measured as a function of the concentration of fluoride catalyst and of nitric acid. Dissolved thorium and aluminum were found to inhibit the reaction. Thoris exhibited penetration rates much lower than those of thorium metal. In addition to the specific rate measurements, pot type batch dissolvings were carried out to estimate plant time cycles. An empirical mathematical equation was devised which correlates the results of these batch dissolvings and facilitates application of the data to other types of dissolvers.

Abstract: A re-evaluation of the cost of producing essentially hafnium free zirconium as zirconium oxide at a rate of 150,000-200,000 pounds zirconium per year by solvent extraction of the metal thiocyanates in a permanent plant has been made. Using part of the present temporary facilities, the cost, with five year amortization of the plant, will be $3.15 per pound zirconium. A by-product of the mixed oxides of hafnium and zirconium, having at least fifty percent hafnium and perhaps as high as ninety percent hafnium, can be made available with little additional cost.

From Summary: "Results are presented of an experimental investigation of the characteristics of NACA submerged inlets on a model of a fighter airplane for Mach numbers from 0.30 to 0.875. The effects on the ram-recovery ratio at the inlets of Mach number, angle of attack, boundary-layer thickness on the fuselage, inlet location, and boundary-layer deflectors are shown. The data indicate only a slight decrease in ram-recovery ratio for the inlets ahead of or just behind the wing leading edge as Mach number increased, but showed large decreases at high Mach numbers for the inlets aft of the point of maximum thickness of the wing."

Report presenting an investigation conducted in the 8- by 6-foot supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Data were obtained for various ejector diameter and spacing ratios at a range of Mach numbers, pressure-ratio ranges, and secondary-primary weight-flow ratios. Results regarding the primary-nozzle mass-flow coefficients, performance comparison of configurations, effect of free-stream Mach number on the ejectors, net thrust characteristics, and comparison to conventional nozzles are provided.

Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.

Two charts are given for each of the gases hydrogen, nitrogen, and oxygen. The first gives directly the number of standard cubic feet of the gas which a cylinder will deliver. The second chart gives values of the compressibility factor and of the density.

"At the request of the Air Materiel Command, Army Air Forces, an investigation of the low-speed, power-off, stability and control characteristics of the McDonnell XP-85 airplane has been conducted in the Langley free-flight tunnel. The results of the portion of the investigation consisting of tests of a 1/10-scale model to study the stability of the XP-85 when attached to the trapeze and during retraction into the B-36 bomb bay are presented herein. In the power-off condition the stability was satisfactory with all oscillations well damped and the nose-restraining collar could be placed in position without difficulty" (p. 1).

Report discussing an investigation of 24 aromatic amines as antiknock additives in aircraft gasolines and their low-temperature solubility.

"Changes, corrections and additions to the original report are included in this addendum. These are brought about by further development of the design by Blaw-Knox, ANL and ORNL. The changes are listed in accordance with the main headings, pages and paragraphs to which they apply."

Report presenting some of the factors affecting the two-dimensional characteristics of flap-type controls equipped with overhang nose balances at a Mach number of 2.40. The effects of changing nose-balance overhang, altering the shape of the nose balance, beveling the afterbody of the basic wing forward of the flap nose, varying wing-flap gap size, fixing transition, and varying the flap trailing-edge thickness are presented.

Report presenting the effect of removal of the boundary layer inside the inlet on the performance of a twin-duct side-air-intake system in the 8- by 6-foot supersonic wind tunnel at a free-stream Mach number of 2.0. Results regarding the internal performance characteristics of inlets, supercritical mass-flow ratio, diffuser total-pressure recovery, and effect of bleeding the boundary layer are provided.

Report presenting a discussion of the flow mechanism in an afterburner extension to a ramjet engine. An experimental evaluation of the operation of 16-inch ramjet equipped with an afterburner at Mach number 1.8 and 2.0 in the supersonic wind tunnel. The experimental data confirmed the proposed method of afterburner operation.

Abstract: "A general description is given of the permanent zirconium plant at Y-12. Equipment is described and materials of construction are listed. Photographs illustrating principal equipment and reduced construction drawings are also presented. Operating conditions and costs information are listed."

Report presenting combustion-efficiency data for a 5-inch-diameter combustor employing a straight V-gutter flame holder and a simple cone flame holder. The data covers a range of inlet static pressures, temperatures, and velocities for four fuels. The majority of the data indicated that the combustion efficiency was relatively insensitive to fuel-air ratio over the range of fuel-air ratios investigated.

The final r.f. characteristics of A-12 are shown. The mechanical features are available in UCRL-1859. If A-12 were to be changed to 24.2 mm rather than 12.1 mm, keeping the same length and the same constant average coil gradient of 0.375 MV/ft., the characteristics of such an A-24 can be obtained from the attached curves.

From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."

Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.

Abstract: Use of the mixer-settler apparatus as a rapid means of determining improved conditions for plant operation is described including the experimental details. The preparation of highly purified samples of both zirconium oxide and hafnium oxide is discussed. (This document is concerned almost entirely with explorations of small scale continuous systems. Another document dealing with this general problem using small scale batch operations is being published simultaneously. It should prove of advantage to the reader to study this companion report, Document Y-611, by Barton, Overholser, and Grimes, to obtain a complete picture of the available information.).

From abstract: "In this report we present data obtained with the optical simulation apparatus on image quality as a function of the parameters of neutron scattering and image detector resolution...Also included in this report is a brief description of a large area (5 inch diameter) neutron beam exposure facility being set up at the reactor for the phase three work."