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Graphite expansion committee meeting of January 10, 1947

Description: The thirteenth meeting of the Graphite Expansion Committee was held on January 10, 1947. A summary of meeting topics follow. The horizontal bowing of Tube 4494-D in the top corner of the pile is considerably greater than the bowing which can be attributed to graphite expansion at this elevation in the pile, indicating that the top layers of graphite are being dragged outward by expansion of the underlying layers. Such a phenomenon could shear the vertical thimbles at a point just below the ther… more
Date: January 23, 1947
Creator: Woods, W. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical requirements of the 234-5 Project

Description: At this time it is desirable that preliminary estimates be made of the manpower, equipment, space, layout and facility requirements of the analytical section for the 234-5 Project. To arrive at these requirements a rough estimate of the required analyses, their scope and their frequency has been compiled. This is expected to serve as a basis for the Laboratories Division to outline their space and equipment requirements as soon as possible and to assemble the required personnel for operation la… more
Date: October 23, 1947
Creator: Work, J.B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An approximate method for calculating the effect of surface roughness on the drag of an airplane

Description: From Summary: "A method for computing the effect of surface roughness on the drag coefficient of an airplane is presented. Calculated results using this method are compared with experimental results from both flight and wind-tunnel tests. In general, the agreement is believed satisfactory."
Date: July 23, 1947
Creator: Hall, Charles F. & Fitzgerald, Fred F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds

Description: Report presenting a method for calculating the drag, in a real compressible fluid and at subcritical Mach numbers, of airfoil sections at arbitrary life coefficients and of bodies of revolution at zero angle of attack. The values of drag coefficient are compared with values obtained for the same configurations by other methods. The differences between the results are found to lie withint he limits of accuracy of current experimental techniques.
Date: April 23, 1947
Creator: Heaslet, Max A. & Nitzberg, Gerald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight-Test Measurements of Aileron Control Surface Behavior at Super Critical Mach Numbers

Description: Report presenting measurements of the behavior at supercritical Mach numbers of ailerons on a jet-propelled fighter plane. Results regarding aileron upfloat and aileron oscillations are provided.
Date: April 23, 1947
Creator: Brown, Harvey H.; Rathert, George A., Jr. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000

Description: Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date: May 23, 1947
Creator: Neely, Robert H. & Conner, D. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Application of Tracer Techniques to the Determination of Uranium Extraction Coefficients

Description: Abstract: This report deals with the development of a method using tracer technique for determining uranium extraction coefficients on solutions of low uranium concentration. It was found that extraction coefficients could be determined on systems containing as low as one part per million uranium using 1900 level uranium as the tracer. Results of several extraction series are presented in which aluminum nitrate is used as the salting agent and dibutyl carbitol the organic extractant.
Date: January 23, 1947
Creator: Lee, D. A.; Woodard, R. W. & Clewett, G. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Submerged Duct Installation on the Ryan FR-1 Airplane in the Ames 40- by 80-Foot Wind Tunnel

Description: "An investigation of an NACA submerged intake installation on the Ryan FR-1 was conducted to determine the full-scale aerodynamic characteristics of this installation. In addition, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance. Stalling of the air flow over the inner lip surface created … more
Date: April 23, 1947
Creator: Martin, Norman J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Estimation of the Spin and Recovery Characteristics of the North American XSN2J-1 Airplane

Description: "The probable spin and recovery characteristics of the XSN2J-1 air-plane have been estimated on the basis of the results of brief test a performed on a model of an airplane of somewhat similar design. The spin-recovery tail-parachute requirements for the airplane were also determined end, in addition, an analysis was made to determine the best method of emergency pilot escape during a spin. The results of the investigation indicate that the recovery characteristics of the airplane will be satis… more
Date: June 23, 1947
Creator: Snyder, Thomas L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling Characteristics of the V-1650-7 Engine, 1, Coolant-Flow Distribution, Cylinder Temperatures, and Heat Rejections at Typical Operating Conditions

Description: From Summary: "An investigation was conducted to determine the coolant-flow distribution, the cylinder temperatures, and the heat rejections of the V-1650-7 engine . The tests were run a t several power levels varying from minimum fuel consumption to war emergency power and at each power level the coolant flows corresponded to the extremes of those likely to be encountered in typical airplane installations, A mixture of 30-percent ethylene glycol and 70-percent water was used as the coolant. T… more
Date: May 23, 1947
Creator: Povolny, John H. & Bogdan, Louis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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