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Processing of Special Metal for Hanford

Description: The object of this project is to reduce the impurities and raise the density of rejected slugs and briquetted turnings from these slugs by recasting the material. Summary and conclusions are (1) slugs and briquettes made from turnings produced when these slugs were machined can be recast with great improvement in quality; (2) casting this material is quite hard on graphite crucibles, but a long-range program might point the way to better graphite usage; (3) this metal run alone gives fair yield… more
Date: March 10, 1947
Creator: Oppold, William A.
Partner: UNT Libraries Government Documents Department
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Reclamation of Contaminated Kinney and Diffusion Pump Oils and Removal of Uranium Therefrom

Description: Abstract: Test distillations were made with Kinney and diffusion pump oils under vacuum in order to determine accurately the temperature range over which satisfactory distillate may be collected. Also recommendations are made as to the most advisable type of heating equipment necessary to produce the required heat and maintain the desired temperature. In addition, several important refinements in the distillation equipment were checked for operational characteristics and for their efficiency in… more
Date: March 10, 1947
Creator: Lee, J. E. Jr.; Aikin, L. M. & Susano, C. D.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Low-Speed Stability and Control Characteristics of Swept-Forward and Swept-Back Wing in the Ames 40- by 80-Foot Wind Tunnel

Description: "An investigation has been made at large scale of the characteristics of highly swept wings. Data were obtained at several angles of sideslip on wings having angles of sweep of plus or minus 45 degrees, plus or minus 30 degrees, and 0 degrees. The airfoil sections of the wings varied from approximately NACA 0015 at the root to NACA 23009 at the tip. Each wing was investigated with flaps under flection, partial-span split flaps deflected 60 degrees, full-span split flaps defected 60 degrees and … more
Date: June 10, 1947
Creator: McCormack, Gerald M. & Stevens, Victor I., Jr.
Partner: UNT Libraries Government Documents Department
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Effect of Chordwise Vanes on Amplitude of Tail Buffeting

Description: "Flight tests have been made with a P-51D airplane to determine the effect of chordwise vanes on the amplitude of tail buffeting. The tests made during abrupt pull-ups to the buffeting boundary included strain measurements on wing and tail and tuft studies over the wing. The results indicate that the vanes tested have no appreciable effect on the amplitude of tail buffeting" (p. 1).
Date: November 10, 1947
Creator: Stokke, Allen R.
Partner: UNT Libraries Government Documents Department
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The Effect of Sample Size on the Determination of Maximum Gust Velocities in Clouds

Description: Report presenting the application of simple sampling procedures to gust data obtained from P-61 thunderstorm flights in Orlando, Florida. The results demonstrated that the observed values of maximum effective gust velocities tend to be functions of the record distance of cloud survey.
Date: October 10, 1947
Creator: Press, Harry
Partner: UNT Libraries Government Documents Department
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An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 2: The Effect of Airfoil Section Modifications and the Determination of the Wake Downwash

Description: Report presenting a study of the characteristics of a large-scale triangular wing to include the effects of section modifications. The wing in this report is the same as the one in the previous report but features various degrees of rounding of the wing leading edge and wing maximum thickness rather than having sharp edges. Results regarding the effects of airfoil section modifications, visible trailing vortices, and surveys in the extended chord plane are provided.
Date: December 10, 1947
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
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An Analysis of Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations During the Early Summer of 1946

Description: Report presenting airspeed and altitude data obtained from Lockheed Constellation airplanes flying between New York and San Francisco during May and June of 1946 in order to determine the probability of reaching or exceeding given values of airspeed and Mach number. Analysis indicated that the total probability of exceeding the placard "never extend" speed depends primarily on the probability of exceeding this speed in descent. The probability of exceeding the critical Mach number is very negli… more
Date: October 10, 1947
Creator: Steiner, Roy
Partner: UNT Libraries Government Documents Department
open access

Analytical Comparison of a Standard Turbojet Engine, a Turbojet Engine with a Tail-Pipe Burner, and a Ram-Jet Engine

Description: From Introduction: "Experimental investigations (reference 1) have shown that in some cases the thrust can be more than doubled by means of tail-pipe burning. A comparison is made of a standard turbojet engine, whose thrust is augmented by tail-pipe burning, and a ram-jet engine. The performance characteristics for the ram-jet engine were computed entirely from theoretical considerations and on the assumption that the burner-inlet velocity was constant."
Date: February 10, 1947
Creator: Krebs, Richard P. & Palasics, John
Partner: UNT Libraries Government Documents Department
open access

Yaw Characteristics and Sidewash Angles of a 42 Degree Sweptback Circular-Arc Wing With a Fuselage and With Leading-Edge and Split Flaps at a Reynolds Number of 5,300,000

Description: Report presenting testing of the low-speed aerodynamic characteristics in yaw of a 42 degree sweptback wing of circular-arc airfoil sections in the pressure tunnel. The wing had an aspect ratio of 3.94, taper ratio of 0.625, and no dihedral or twist. Results regarding lateral-stability parameters of plain wing, effect of wing flaps on lateral-stability parameters, effect of fuselage on lateral-stability parameters, a comparison with the NACA 64(sub 1)-112 wing, characteristics in the extended y… more
Date: December 10, 1947
Creator: Salmi, Reino J. & Fitzpatrick, James E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Loads on a Typical Bubble-Type Canopy

Description: Report presenting an investigation of the surface pressures of the outer and inner surface of the bubble-type canopy in order to determine their load requirements. Testing was performed on a Grumman F8F-1 airplane. The forces on the canopy was found to be the highest when the airplane is operating at high speed with the canopy closed.
Date: July 10, 1947
Creator: Cocke, Bennie W., Jr.
Partner: UNT Libraries Government Documents Department
open access

The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions

Description: Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.
Date: April 10, 1947
Creator: Allen, H. Julian; Heaslet, Max A. & Nitzberg, Gerald E.
Partner: UNT Libraries Government Documents Department
open access

The interdependence of various types of autoignition and knock

Description: A study of the relations existing among pin-point autoignition, homogeneous autoignition, and knock has been made by means of the NACA high-speed camera and the full-view combustion apparatus. High-speed photographic records of combustion, together with corresponding pressure-time traces, of benzene, 2,2,3-trimethylbutane, S-4, and M-4 fuels at various engine conditions have shown the engine conditions under which each of these phenomena occur and the relation of these phenomena to one another.
Date: February 10, 1947
Creator: Olsen, H. Lowell & Miller, Cearcy D.
Partner: UNT Libraries Government Documents Department
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Interference Method for Obtaining the Potential Flow Past an Arbitrary Cascade of Airfoils

Description: "A procedure is presented for obtaining the pressure distribution on an arbitrary airfoil section in cascade in a two-dimensional, incompressible, and nonviscous flow. The method considers directly the influence on a given airfoil of the rest of the cascade and evaluates this interference by an iterative process, which appeared to converge rapidly in the cases tried (about unit solidity, stagger angles of 0 degree and 45 degrees). Two variations of the basic interference calculations are descri… more
Date: January 10, 1947
Creator: Katzoff, S.; Finn, Robert S. & Laurence, James C.
Partner: UNT Libraries Government Documents Department
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Preparation of 1-C14-Propene-1 and the Mechanism of Permanganate Oxidation of Propene

Description: 1-C{sup 14}-propene has been prepared. The migration of the double bond under a variety of experimental conditions in the preparation of propene has been investigated. The mechanism of the permanganate oxidation of the labeled propene has been examined; it has been found to proceed by several paths, the relative importance of which depends upon the experimental conditions, especially the pH.
Date: December 10, 1947
Creator: Fries, B. A. & Calvin, M.
Partner: UNT Libraries Government Documents Department
open access

Effects of Pile Radiation on Be Metal

Description: The following report examines a set of beryllium metal rods through pile radiation, taking measurements, and analyzing differences between irradiated and radiated rod samples.
Date: June 10, 1947
Creator: Siegel, Sidney
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel Part 5 - Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage TED No. NACA DE308, Part V, Wing-Alone Tests and Effect of Modifications to the Vertical Fins, Speed Brakes, and Fuselage, TED No. NACA DE308

Description: "Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The wing-alone tests and the effect of the various vertical-fin modifications, speed-brake modifications, and fuselage modifications on the aerodynamic characteristics in pitch and yaw are presented in the present paper with a limited analysis of the results. Also i… more
Date: October 10, 1947
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department
open access

Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Fairchild Lark Pilotless-Aircraft Configuration. Static Longitudinal Stability of Models with Wing Flap Deflections of 0 Deg and 15 Deg, TED No. NACA 2387

Description: From flight tests of 0.5-scale models of the Fairchild Lark pilotless aircraft conducted at the flight test station of the Pilotless Aircraft Research Division at Wallops Island, Va., some evaluations of the static longitudinal stability were obtained by analysis of the short-period oscillations induced by the abrupt movement of the rudder elevators. The analysis shows that for the Lark configuration with wing flap deflections of 0 degrees and 15 degrees the static longitudinal stability decrea… more
Date: January 10, 1947
Creator: Stone, David G.
Partner: UNT Libraries Government Documents Department
open access

Tuft Studies of the Flow over a Wing at Four Angles of Sweep

Description: Studies of the stalling characteristics show that the stall begins at the tip and moves inboard with increasing angle of attack at positive sweep; the sta11 begins at root and moves outboard at negative sweep (sweepforward). At +/-45 deg sweep the stall was less sharply defined than at the lower angles of sweep. No effect of Mach number on the.flow patterns as indicated by tufts was found in the speed range of these tests which extended to a Mach number of 0.55.
Date: July 10, 1947
Creator: Hieser, Gerald
Partner: UNT Libraries Government Documents Department
open access

Supplementary Data on Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations

Description: "A total of 197 hours of time histories of airspeed and altitude have been obtained on Lockheed Constellation airplanes flying between New York, N.Y. and San Francisco, Calif. during May 1946 and June 1946. Data for 130 hours were previously analyzed to determine the probability of attaining excessive airspeeds and Mach numbers and the results have been published. After the publication, data for additional 67 hours became available" (p. 1).
Date: October 10, 1947
Creator: Steiner, Roy
Partner: UNT Libraries Government Documents Department
open access

Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000

Description: Wind-tunnel investigations were made in pitch and yaw with and without split flaps. Presence of the fuselage had negligible effect on values of maximum lift coefficient and slope of lift curve, but caused a destabilizing shift in the rate of change of pitching moment with lift. Effects of fuselage position on drag characteristics were small for wings without flaps, but were appreciable when split flaps were on.
Date: June 10, 1947
Creator: Salmi, Reino J.; Conner, D. William & Graham, Robert R.
Partner: UNT Libraries Government Documents Department
open access

Effect of Air-Flow Distribution and Total-Pressure Loss on Performance of One-Sixth Segment of Turbojet Combuster

Description: "An investigation has been conducted on a one-sixth segment of an annular turbojet combustor to determine the effects of modification in air-flow distribution and total-pressure loss on the performance of the segment. The performance features investigated during this series of determinations were the altitude operational limits and the temperature-rise efficiency. Altitude operational limits of the combustor segment, for the 19XB engine using the original combustor-basket design were approximat… more
Date: December 10, 1947
Creator: Hill, Francis U. & Mark, Herman
Partner: UNT Libraries Government Documents Department
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