Introduction: "Room temperature and elevated temperature, static immersion and vapor suspicion, corrosion tests were conducted with Duriron, Hastelloy C, and tantalum in hydriotic acid and 234-5 project process supernatant solution (synthetic environments. The data relevant to these tests are contained herein."

"A method of predicting equilibrium operating performance of turbojet engines has been developed, with the assumption of simple model processes for the components. Results of the analysis are plotted in terms of dimensionless parameters comprising critical engine dimensions and over-all operating variables. This investigation was made of an engine in which the ratio of axial inlet-air velocity to compressor-tip velocity is constant, which approximates turbojet engines with axial-flow compressors" (p. 673).

This report details events of importance reported by the Hanford Operations Office for the week ending February 23, 1949.

This document details activities at the Hanford Engineer Works during the month of January 1949.

"The spin and recovery characteristics of the Northrop XF-89 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape are presented in this report. The characteristics were mainly estimated rather than determined by model tests because the XF-89 dimensional and mass characteristics were such as to make this airplane similar to several others, models of which have previously been tested. Brief tests were made on an available model of similar design to augment the estimation" (p. 1).

Report discussing a particular wing-body combination that is part of a larger investigation to determine the lift, drag, pitching moment, and root bending moments for various configurations. Information about the aerodynamic characteristics at the tail plane is also provided.

Report presenting an investigation of the pressure distribution on an asymmetrical nonconical body at a Mach number of 1.90 over a wide range of angles of attack and yaw. Pressure distributions occurred at anticipated trends. Results regarding the pressure coefficients, Schileren photographs, boundary layers, and pressure distributions are provided.

None

Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.

Report presenting an investigation in the two-dimensional low-turbulence tunnel of the NACA 65,3-418 airfoil section with a 25-percent-airfoil-chord plain flap and a suction slot on the flap. The primary purpose of the investigation is to determine the effect of the type of boundary-layer control on the section lift-drag ratio.

The attenuation of electro-statically and electro-magnetically shielded rooms in the ``E,`` ``R,`` ``I,`` and ``T`` Buildings was measured so that corrective measure could be taken if the attenuation was found to be low. If remedial measures could not be taken, the shortcomings of the rooms would be known. Also, the men making the measurements should oversee construction and correct errors at the time. The work was performed by measuring the attenuation at spot frequencies over the range of from 150 kilocycles to 1280 megacycles with suitable equipment mounted in small rubber-tried trucks. The attenuation was determined by ``before and after`` shielding and/or ``door open and door closed`` measurements after installation of copper shielding. In general, attenuation in the frequency range of approximately 10 to 150 mc. was good and was of the order expected. At frequencies in the range of 150 mc. to 1280 mc., the attenuation curve was more erratic; that is, at certain frequencies a severe loss of attenuation was noted, while at others, the attenuation was very good. This was mainly due to poor or faulty seals around doors and pass windows. These poor seals existed in the ``T,`` ``E,`` and ``I`` Buildings because the doors were …

This report details events of importance reported by the Hanford Operations Office for the week ending February 16, 1949.

Report presenting the damping-in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings in the 9-inch supersonic wind tunnel. The damping in roll of the rectangular wings was very close to what was predicted by linear theory, but the triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind the Mach cone.

From Summary: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil-angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders."

From Summary: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil-angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders."

"The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders" (p. 1).

Report presenting testing of three rocket-powered models with Douglas D-558-2 wings as horizontal fins with scaled structural parameters to determine whether the possibility of wing flutter due to torsion and bending exists in full-scale airplanes at transonic speeds. No wing flutter was present in the models tested, but pitching oscillation developed as it passed into the transonic range.

Abstract: "Following nitrate removal by means of a three-stage hydrochloric acid digestion, uranium was reduced with chromous sulfate reagent. In an inert atmosphere, the quadrivalent uranium was titrated at 80-95[degrees] with standard ferric sulfate solution. The end point was obtained with a potentiometric cell including a platinum in-titrant reference electrode and a platinum indicator electrode. Application was made to various low leverl uranium solutions. For samples containing 1 - 12 milligrams or uranium, less than one percent error may be expected. Iron and chromium do not interfere."

Despite the fact the adequate data from long-term, chronic experiments on the effects of Po{sup 210} are not available, some sort of a working figure for the maximum permissible body content of polonium is desirable. As described herein, calculations involved in determining the permissible body content of polonium generally fall into three classes. 1. Comparison of X-ray and polonium toxicity and application of an acceptable X-ray tolerance figure. 2. Assumption of a most sensitive organ and computation of the critical concentration of radioactive material present in this organ under conditions such that the organ received an assumed maximum permissible exposure over an indefinitely long period of time. 3. Comparison of radium and polonium toxicity with application of an acceptable maximal content of radium.

Activities covered in this report for the month of January are as follows: (1) power coefficient test of the F Pile; (2) control rod calibration; (3) investigations into reactivity gains possible by zoning the pile for metal charging; (4) polonium production under emergency conditions: (5) analysis of process tube ion chamber failures; (6) measurements of the thermal neutron flux in various pockets of the E Test Hole of the F Pile; (7) reactivity balance of each of the operating piles at beginning and end of this report period; (8) graphite studies; (9) pile shielding; (10) radiation measurements on a simulated D-R rod guide and rod; and (11) calculation of radioactive isotopes expected in cooling water.

Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.

The Purpose of this manual is to describe preparation of bismuth powder for use in process operations. Bismuth powder is to be prepared in Room 232 of ``T`` Building where all necessary apparatus is installed.

None

Abstract: Processes are described for preparing small samples of 42 wt. % U-Al alloy (uranium enriched with U235) for pile irradiation studies. In the course of this work it was found that the size of the massive Al-U grains remains substantially unaltered during hot rolling.