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THE HEAT CAPACITY OF U$sub 3$O$sub 8$ POWDER AS A FUNCTION OF TEMPERATURE (400-1800 F)

Description: The mean heat capacity of a sample of powdered U/sub 3/O/sub 8/ was determined as a function of temperature from measurements of heat content. A thin-walled nickel capsule containing the material was heated in an electric furnace and dropped into a water calorimeter The Mean heat capacity values calculated from the experimental data were nearly constant over the temperature range, room temperture to 250-975 deg C (482-1790 deg F). The average value was 0.074 plus or minus 0.004 cal gm/sup -1EDE… more
Date: April 26, 1949
Creator: Powers, H.; Welch, F. & Trice, J.B.
Partner: UNT Libraries Government Documents Department
open access

Hanford Works Monthly Report: December 1948

Description: This document details activities at the Hanford Engineer Works during the month of December 1948.
Date: January 26, 1949
Creator: Muir, R. C.
Partner: UNT Libraries Government Documents Department
open access

The reversibility theorem for thin airfoils in subsonic and supersonic flow

Description: A method introduced by Munk is extended to prove that the light-curve slope of thin wings in either subsonic flow or supersonic flow is the same when the direction of flight of the wing is reversed. It is also shown that the wing reversal does not change the thickness drag, damping-in-roll parameter or the damping-in-pitch parameter.
Date: June 26, 1949
Creator: Brown, Clinton E.
Partner: UNT Libraries Government Documents Department
open access

A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing

Description: Report presenting a review of the status of instruments suitable for the measurement of the meteorological factors conducive to aircraft icing. Nine instruments which appear to be the most promising for obtaining meteorological data are discussed and recommendations for their continued use and development are provided.
Date: April 26, 1949
Creator: Jones, Alun R. & Lewis, William
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speeds of Various Plug-Aileron and Lift-Flap Configurations on a 42 Degree Sweptback Semispan Wing

Description: Report presenting a wind-tunnel investigation on a 42 degree sweptback-wing model to determine the lateral control characteristics of a plug-aileron configuration. The configuration consisted of six segments extending from the wing 20-percent-span to the wing 80-percent-span stations and with the center of each plug on the wing 70-percent-chord line. Results regarding wing aerodynamic characteristics and lateral control characteristics are provided.
Date: January 26, 1949
Creator: Schneiter, Leslie E. & Watson, James M.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at a Mach number of 1.53 including effect of small variations of sweep

Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable … more
Date: January 26, 1949
Creator: Madden, Robert T.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 2: nacelle with long straight air inlet

Description: Report presenting aerodynamic and icing investigations conducted in the icing research tunnel on a model of a turbojet-engine nacelle with a long straight air inlet in order to provide basic design criteria for hot-gas blowback systems. The most uniform temperature distribution was obtained with a bleedback of 4.4 percent at a gas temperature of 1000 degrees Fahrenheit and resulted in an average dry-air-temperature rise of 46 degrees Fahrenheit.
Date: May 26, 1949
Creator: Callaghan, Edmund E. & Ruggeri, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Effects of systematic changes of trailing-edge angle and leading-edge radius on the variation with Mach number of the aerodynamic characteristics of a 10-percent-chord-thick NACA airfoil section

Description: Report presenting the results of a wind-tunnel investigation of the effects of variation of trailing-edge angle and leading-edge radius on the aerodynamic characteristics of a 10-percent-chord-thick airfoil section at a range of Mach numbers.
Date: September 26, 1949
Creator: Summers, James L. & Graham, Donald J.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 2: 18.41-Inch-Diameter Jet Nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.
Date: October 26, 1949
Creator: Armstrong, J. C.; Wilsted, H. D. & Vincent, K. R.
Partner: UNT Libraries Government Documents Department
open access

Study by NACA Wing-Flow Method of Transonic Drag Characteristics of a Blunt-Nose Body of Revolution and Comparison with Results for a Sharp-Nose Body

Description: Memorandum presenting a study of a body of revolution with an NACA 1-50-100 nose inlet at zero angle of attack and no internal air flow to study the pressure drag of an extremely blunt-nose body and comparison with previous results for a sharp-nose body. The change from sharp to inlet nose while maintaining the same afterbody shape decreased the drag-rise Mach number from 0.94 to 0.90.
Date: April 26, 1949
Creator: Johnston, J. Ford & Lopatoff, Mitchell
Partner: UNT Libraries Government Documents Department
open access

Investigation of several clamshell variable-area exhaust nozzles for turbojet engines

Description: Report presenting the results of several investigations of the performance of different types of clamshell variable-area exhaust nozzle far turbojet engines to determine the efficiency of that type of exhaust nozzle as compared with conventional fixed-area conical exhaust nozzles. The investigations were conducted at zero-ram sea level conditions on three different full-scale turbojet engines and using five different nozzles.
Date: May 26, 1949
Creator: Lundin, Bruce T.
Partner: UNT Libraries Government Documents Department
open access

Influence of chemical composition on rupture properties at 1200 degrees F of forged chromium-cobalt-nickel-iron base alloys in solution-treated and aged condition

Description: From Summary: "The influence of systematic variations of chemical composition on rupture properties at 1200 degrees F. was determined for 62 modifications of a basic alloy containing 20 percent chromium, 20 percent nickel, 20 percent cobalt, 3 percent molybdenum, 2 percent tungsten, 1 percent columbium, 0.15 percent carbon, 1.7 percent manganese, 0.5 percent silicon, 0.12 percent nitrogen and the balance iron. These modifications included individual variations of each of 10 elements present and… more
Date: October 26, 1949
Creator: Reynolds, E. E.; Freeman, J. W. & White, A. E.
Partner: UNT Libraries Government Documents Department
open access

Progress Report: June 1949: Preparation of Ductile Zirconium

Description: Report discussing progress made in testing methods for preparation of ductile zirconium by the National Research Corporation for the month of June, 1949.
Date: July 26, 1949
Creator: DiPietro, W. O.; Findlay, G. R. & Mellen, G. L.
Partner: UNT Libraries Government Documents Department
open access

Asphalt as a Shielding Medium C-300

Description: The following document analyzes studies to test the use of asphalt as a fast neutron moderating substance to be incorporated as a part of a pile shield.
Date: September 26, 1949
Creator: Jaske, R. T.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds, 1, Stability and Control Characteristics

Description: Wind tunnel tests of the 0.16-scale Douglas MX-656 model were made at low and high subsonic Mach numbers to investigate the static longitudinal- and lateral stability characteristics. The tests shows that undesirable changes in longitudinal stability at the stall were apparently caused by an altered downwash pattern at the tail. The jettisonable nose fins were highly destabilizing. Compressibility effects for the test Mach numbers were not detrimental to the longitudinal- or lateral-stability c… more
Date: April 26, 1949
Creator: Hamilton, William T. & Cleary, Joseph W.
Partner: UNT Libraries Government Documents Department
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