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Investigation of contamination bearing algae in the Columbia River

Description: Recent discussions in the group have given rise to the problem of determining whether the beta contamination found in the Columbia River is carried by the algae which are found in the retention basin. The algae accumulate in the basin and apparently remain there longer than the retained water, and thus may be contaminated to a greater extent than the water itself.
Date: October 13, 1947
Creator: Paas, H. J.
Partner: UNT Libraries Government Documents Department
open access

Graphite expansion committee meeting of June 6, 1947

Description: The gas thermometer in the F Pile has been overhauled and re-calibrated. The readings are still in agreement with the readings from the graphite thermocouples. A similar overhaul of the gas thermometer in the D Pile will be made during June. The progress of further outward bowing of Tube 2496-D can not be followed satisfactorily even though readings are obtained from both inlet and outlet ends of the tube. Preliminary results obtained from the one-tube mock-up suggest the possibility that the g… more
Date: June 13, 1947
Creator: Woods, W. K.
Partner: UNT Libraries Government Documents Department
open access

Distribution of Boron in Processing of Carnotite Concentrate

Description: It was desired to determine the distribution of boron in the various steps of the processing of domestic ore concentrates containing high percentages of boron. The experiments described in this report were directed toward that end. Summary of this report are: (1) a black oxide containing 0.6 ppm of boron was prepared from material containing 350 ppm; (2) less than 0.02% of the boron in the original material appeared in the black oxide; (3) the iron step did not remove appreciable amounts of bor… more
Date: March 13, 1947
Creator: O'Connors, R. J.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of velocity distributions of downstream of single duct bends

Description: Report presenting measurements of the velocity distributions at the outlet of a large number of duct elbows of round and elliptical as well as square and rectangular cross section at a range of Reynolds numbers. Special investigations include measurements of the decay of velocity patterns produced by curved ducts and the effect of asymmetrical upstream velocity distributions. Results regarding typical distributions, tabulation of principal results, and special investigations are provided.
Date: January 13, 1947
Creator: Weske, John R.
Partner: UNT Libraries Government Documents Department
open access

Investigation of shock diffusers at Mach number 1.85 3: multiple-shock and curved-contour projecting cones

Description: Report presenting total-pressure recoveries obtained with four-cone inlet combinations at Mach number 1.85. The configurations tested included a cone designed to produce three oblique shocks ahead of the diffuser inlet combined with two other inlets, a cone generated by a parabolic arc in combination with two other inlets, a cone-inlet combination designed to produce an isentropic entrance flow at 0 degrees angle of attack, and a 30 degree single-shock cone combined with a perforated inlet sect… more
Date: August 13, 1947
Creator: Moeckel, W. E. & Connors, J. F.
Partner: UNT Libraries Government Documents Department
open access

An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings

Description: Report presenting an investigation of the effect of tip shape on the aerodynamic characteristics of large-scale 45 degrees swept-forward and 45 degrees swept-back wings. The results show that none of the variations of tip shape investigated nor the addition of bodies of revolution at the tips produced major changes in the characteristics of the swept wings.
Date: November 13, 1947
Creator: Walling, Walter C.
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation of Fullspan, 0.2 Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Taper, Aspect Ratio, and Section-Thickness Ratio

Description: Report presenting an aerodynamic-control-effectiveness investigation using free-flight rocket-propelled RM-5 test vehicles at high subsonic, transonic, and supersonic speeds. Results regarding aileron control characteristics and drag measurements are provided.
Date: August 13, 1947
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department
open access

Drag of a Wing-Body Configuration Consisting of a Swept-Forward Tapered Wing Mounted on a Body of Fineness Ratio 12 Measured During Free Fall at Transonic Speeds

Description: Report discussing an investigation to determine the drag of a configuration with a body of fitness ratio 12 with stabilizing tail surfaces and a 12-percent-thick 30-degree swept-forward wing using the free-fall method. The drag oft he wing and the total drag were measured separately and compared. The swept-forward wing was found to greatly increase the effect of drag on the body-tail combination.
Date: March 13, 1947
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Characteristics in Pitch of a 42 Degree Sweptback Wing With Aspect Ratio 3.9 and Circular-Arc Airfoil Sections

Description: Report presenting tests in a pressure tunnel to determine the low-speed pitch characteristics of a 42 degree sweptback wing with circular-arc airfoil sections. Information regarding the characteristics of basic wing, leading-edge flap investigation, and effects of fuselage are provided.
Date: November 13, 1947
Creator: Neely, Robert H. & Koven, William
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds

Description: Report presenting the results of tests to determine the effect of taper on the zero-lift drag of wings of constant exposed aspect ratio at low supersonic speeds. Findings indicated that maximum thickness, leading-edge, and trailing-edge sweep are all important in determining the drag coefficient of a tapered wing.
Date: July 13, 1947
Creator: Alexander, Sidney R. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department
open access

Effect of afterbody length and keel angle on minimum depth of step for landing stability and on take-off stability of a flying boat

Description: From Summary: "Tests were made to fill partly the need for information on the effect of afterbody dimensions on the hydrodynamic stability of a flying boat in smooth water. The dimensions investigated were depth of step, angle of afterbody keel, and length of afterbody. An analysis of the data showed that as either the afterbody length or keel angle was increased an accompanying increase in depth of step was required in order to maintain adequate landing stability."
Date: November 13, 1947
Creator: Olson, Roland E. & Land, Norman S.
Partner: UNT Libraries Government Documents Department
open access

Supplementary Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the McDonnell XB-85 Airplane Equipped with a Conventional-Tail Arrangement

Description: "Spin tests have been conducted in the Langley free-spinning tunnel on a 1/16-scale model of the McDonnell XP-85 airplane with the normal X-tail replaced with a short-coupled conventional tail arrangement. The effect of the conventional tail arrangement and the effects of various modifications upon the spin and recovery characteristics of the model were determined. The results of the tests indicated that installation of the conventional tail arrangement will not provide satisfactory recoveries … more
Date: October 13, 1947
Creator: Klinar, Walter J.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane

Description: "Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data" (p. 1).
Date: February 13, 1947
Creator: Bunnell, Mort V. & Delany, Noel K.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 4 - Compressor and Turbine Performance Characteristics

Description: "As part of an investigation of the performance and operational characteristics of the TG-100A gas turbine-propeller engine, conducted in the Cleveland altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at a compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 to 2100R. The highest compressor pressure … more
Date: November 13, 1947
Creator: Wallner, Lewis E. & Saari, Martin J.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 3 - Pressure and Temperature Distributions

Description: An altitude-wind-tunnel investigation of a TG-100A gas turbine-propeller engine was performed. Pressure and temperature data were obtained at altitudes from 5000 to 35000 feet, compressor inlet ram-pressure ratios from 1.00 to 1.17, and engine speeds from 800 to 13000 rpm. The effect of engine speed, shaft horsepower, and compressor-inlet ram-pressure ratio on pressure and temperature distribution at each measuring station are presented graphically.
Date: November 13, 1947
Creator: Geisenheyner, Robert M. & Berdysz, Joseph J.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at High Speeds of Full-Scale Propellers Having Different Shank Designs

Description: "Tests of two 10-foot-diameter two-blade propellers which differed only in shank design have been made in the Langley 16-foot high-speed tunnel. The propellers are designated by their blade design numbers, NACA 10-(5)(08)-03, which had aerodynamically efficient airfoil shank sections, and NACA 10-(5)(08)-03R which had thick cylindrical shank sections typical of conventional blades. The propellers mere tested on a 2000-horsepower dynamometer through a range of blade-angles from 20 degrees to 55 … more
Date: February 13, 1947
Creator: Maynard, Julian D.
Partner: UNT Libraries Government Documents Department
open access

An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

Description: "Requirements of an automatic engine control, as affected by engine characteristics, have been analyzed for a direct-coupled turbojet engine. Control parameters for various conditions of engine operation are discussed. A hypothetical engine control is presented to illustrate the use of these parameters. An adjustable speed governor was found to offer a desirable method of over-all engine control. The selection of a minimum value of fuel flow was found to offer a means of preventing unstable bur… more
Date: June 13, 1947
Creator: Novik, David & Otto, Edward W.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Description: "An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in … more
Date: March 13, 1947
Creator: Riebe, John M. & Naeseth, Rodger L.
Partner: UNT Libraries Government Documents Department
open access

Performance Investigation of TG-180 Combustor: 1 - Instrumentation, Altitude Operational Limits and Combustion Efficiency

Description: A brief investigation has been made of the performance of a single combustor of the TG-180 turboJet engine to determine (a) the altitude operational limits of the engine for two fuels (AN-F-32 and AN-F-28), (b) combustion efficiencies at various simulated conditions of altitude and engine speeds, (c) combustion-outlet temperature distribution for several altitudes at constant engine speed, and (d) the combustor total pressure drop The limits with AN-83-F-32 fuel were found to be approximately 6… more
Date: January 13, 1947
Creator: Zettle, Eugene V. & Cook, William P.
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 1: Characteristics of a Wing Having a Double-Wedge Airfoil Section With Maximum Thickness at 20-Percent Chord

Description: Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.
Date: November 13, 1947
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
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