Errata sheet for a report issued by the National Bureau of Standards containing corrections to be added to NBS Bulletin 144.

Report discussing the redetermination of liquids for aluminum alloys containing 13 to 25 w/o uranium by metallographic examination, thermal analyses, and electrical resistance measurements. In addition, phase diagrams and a method for producing sound, homogeneous aluminum 16 w/o uranium alloy sleeve castings are presented.

The following objectives were planned for this project. (1) Development of spinning data necessary for spinning Columbium and Columbium-1% Zirconium tubing from ingot, forged or welded tube blanks. (2) Determine mechanical & metallurgical properties of spun Columbium and Columbium-1% Zirconium tubing. (3) Determine dimensional and tolerance limits possible to attain on spun Columbium and Columbium-1% Zirconium tubing based on our present equipment, tooling limitations, and the spinning tests performed for objective No. 1.

Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.

Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.

Report presenting the steady-state performance of the YJ73-GE-3 turbojet engine in an altitude test chamber for a range of exhaust-nozzle areas, simulated altitudes, and Mach numbers. A method of performance calculation based on engine pumping characteristics is provided. Results regarding performance maps, pumping characteristics and performance prediction, thrust correlation, effect of inlet temperature on performance, calculated performance from pumping characteristics, and altitude-ignition characteristics are provided.

Report presents the results of an investigation conducted to determine the hydrodynamic forces and moments acting on modified rectangular flat plates with aspect ratios of 1.00, 0.25, and 0.125 mounted on a single strut and operating at several depths of submersion. A simple method has been developed by modification of Falkner's vortex-lattice theory which enables the prediction of the lift characteristics in unseparated flow at large depths. This method shows good agreement with experimental data from the present tests and with aerodynamic data at all angles investigated for aspect ratios of 1.00 and 0.25 and at angles up to 16 degrees for aspect ratio 0.125. Above 16 degrees for aspect ratio 0.125, the predicted lift proved too high.

Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.

Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.

"A tip section of a delta wing having an NACA 0004-65 airfoil section and a 600 leading-edge sweepback was equipped with a porous leading-edge section through which hot gas was bled for anti-icing. Heating rates for anti-icing were determined for a wide range of icing conditions. The effects of gas flow through the porous leading-edge section on airfoil pressure distribution and drag in dry air were investigated" (p. 1).

Report presenting a flight investigation conducted on a rectangular ramjet incorporating a V-shaped gutter-type flame holder over a range of fuel air ratios, combustion chamber inlet velocities, and pressure altitudes.

Report presenting an investigation of various external-store configurations on a model of a tailless airplane with a sweptback wing over a range of Mach numbers. The investigation was performed out of a desire to reduce the drag interference caused by external stores as much as possible. Results regarding the aerodynamic characteristics in pitch, lift-drag ratios, effect of Mach number, variation of control effectiveness, aerodynamic characteristics in yaw, and variation of stability parameters are provided.

Report presenting an investigation of two NACA 6-series airfoils, the NACA 64(sub)1-212 and NACA 65A109 with leading edge slats and split flaps deflected 60 degrees. Information about optimum slat positions, airfoil section lift characteristics, pitching-moment characteristics, and effect of roughness on the lift characteristics was obtained.

Report presenting an experimental investigation to determine the force and pressure characteristics of a typical nose inlet ramjet configuration. It consisted of a conical spike all-external compression inlet attached to an annular subsonic diffuser. Results regarding external-flow characteristics and internal-flow characteristics are provided.

From Summary: "An experimental technique has been developed which enables a determination of the net propulsive force acting on an afterburner-equipped airplane in flight. The thrust measurement is based on the variation of static and total pressure and stagnation temperature across the fuselage exit as determined by a swinging pitot-static pressure and temperature probe. The details are also presented for an air-cooled fixed-pressure probe for the determination of basic engine thrust."

From Summary: "With low-freezing red fuming nitric acid in a modified open-cup apparatus, ignition delays were determined in the temperature range -40 degrees to -105 degrees Fahrenheit for allylamine, disallylamine, mixed alkyl thiophosphites, ethylenimine, blends of each of these fuels with triethylamine, and blends of ehtylenimine with n-heptane. The data indicate that allylamine, mixed alkyl thiophosphites, and ehtylenimine can be blended with as much as 70 percent triethylamine and still ignite with average delays less than 30 milliseconds at -40 degrees Fahrenheit, and approximately 40 milliseconds at -76 degrees Fahrenheit (-60 degrees Celsius)."

"Flight measurements of the aerodynamic wing and tail loads have been made on the Douglas D-558-II airplane from which the distribution of the aerodynamic load among the wing, fuselage, and horizontal tail has been determined at Mach numbers up to 0.87. These measurements indicate that, for normal-force coefficients less than 0.7, the distribution of air load among the airplane components does not change appreciably with Mach number at Mach number up to 0.87. The measurements also indicate that, for all flight configurations, the increase in airplane normal-force coefficient above the angle of attack at which the wing reaches its maximum normal-force coefficient is due principally to the contribution of the fuselage to the airplane normal-force coefficient" (p. 1).

Report presenting an investigation in the supersonic wind tunnel on an inlet employing conical flow separation from a probe extending upstream from a hemispherical-nosed centerbody. Pressure-recovery and drag characteristics for the inlet were very nearly comparable with a conical-spike inlet, but compared less favorably at Mach numbers below 2.0. A large reduction in pressure recovery and mass flow was obtained at angle of attack.

A low-scale wind-tunnel investigation was conducted in rolling flow to determine the effects of aspect ratio and sweep (when varied independently) on the rolling stability derivatives for a series of untapered wings. The rolling-flow equipment of the Langley stability tunnel was used for the tests. The data of the investigation have been used to develop a method of accounting for the effects of the drag on the yawing moment due to rolling throughout the lift range.

Report presenting an investigation in the stability tunnel to determine the low-speed yawing derivatives of a 0.085-scale model of the Chance Vought XF8U-1 airplane and to determine the static longitudinal and static lateral stability characteristics in order to provide a basis for comparison with other data sources.

Report describes the development of the Langley annular transonic tunnel, a facility in which test Mach numbers from 0.6 to slightly over 1.0 are achieved by rotating the test model in an annular passage between two concentric cylinders. Data obtained for two-dimensional airfoil models in the Langley annular transonic tunnel at subsonic and sonic speeds are shown to be in reasonable agreement with experimental data from other sources and with theory when comparisons are made for nonlifting conditions or for equal normal-force coefficients rather than for equal angles of attack. The trends of pressure distributions obtained from measurements in the Langley annular transonic tunnel are consistent with distributions calculated for Prandtl-Meyer flow.

Report presenting an investigation of the effect of longitudinal body fences on the performance of a top-inlet-fuselage combination in the 8- by 6-foot supersonic wind tunnel. The investigation was conducted at a range of Mach numbers, angles of attack, and a range of inlet mass-flow ratios. The thrust-minus-drag of the top-inlet configuration with fences was higher than the bottom-inlet configuration without fences over most of the range, with the reverse being true at all lift coefficients at Mach 2.0 and higher lift at Mach 1.8.

Report presenting an investigation of the spin and recovery characteristics of a 1/20-scale dynamic model of the Douglas A4D-1 attack airplane in the 20-foot free-spinning tunnel. Erect spins and recoveries were investigated with the model in the clean condition and the loading condition, which includes a center external store with and without two external wing fuel tanks installed. Results regarding several conditions, including erect spins, no external stores, horizontal-tail incidence, 4 degrees leading edge up; erect spins, stores installed; landing conditions, inverted spins, spin-recovery parachute tests, and recommended recovery technique and control forces are provided.

Abstract: "This is the preliminary report of a radiological-ecological survey of the invertebrate fauna that inhabit the Columbia River within the confines of Hanford Works and downstream to the site of McNary Dam. The survey was carried out during the period of October, 1948 through February, 1950. Materials and methods are discussed and the results of extensive radioassays, qualitative and quantitative biological determinations, and hydrographic studies are given and analyzed. Twelve figures and twenty-three tables are included. All aquatic invertebrates were found to be concentrating radioactivity from the river water. A maximum activity density of 4.4-10-(-3) μc/g wet weight was found in the larvae of midges (Hydrobaeninae) collected near Hanford during September, 1949. Radioactive wastes were not found to be causing any apparent deleterious effects to the natural invertebrate fauna. Existing population variations are caused by biological and hydrographic conditions."