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A MEASUREMENT OF THE POSITIVE pi- Mu DECAY LIFETIME

Description: The lifetime for the decay of a {pi} meson into {mu} meson and neutral particle was first measured by Richardson and later by Martinelli and Panofsky. The method was the same in both cases: The fraction of {pi} mesons surviving various times of flight is measured by placing photographic detectors at various path lengths from the target. In the experiment reported here we observe the time lag between the two bursts of fluorescence due to mesons decaying in a scintillation crystal. The first burs… more
Date: May 10, 1950
Creator: Chamberlain, O.; Mozely, R.F.; Steinberger, J. & Wiegand, C.
Partner: UNT Libraries Government Documents Department
open access

The Determination of Total Plutonium in the Presence of Aluminum

Description: Introduction: "The adoption of aluminum nitrate as salting agent in the Redox process made it imperative that a method be available for determining plutonium in the presence of aluminum. However, large amounts of aluminum have been found to interfere with the determination of plutonium by the lanthanum fluoride procedure. Previous attempts to increase the accuracy of the lanthanum fluoride method, by precipitating LaF3 from 4 M HF (rather than 2 M), have been successful only when the initial pl… more
Date: February 10, 1950
Creator: Burns, R. E. & Barton, G. B.
Partner: UNT Libraries Government Documents Department
open access

URANIUM HYDRIDE: A SURVEY

Description: No Description Available.
Date: April 10, 1950
Creator: Kitzes, A.S.
Partner: UNT Libraries Government Documents Department
open access

Uranium Hydride : A Survey

Description: The following report discusses the results of a survey that was initiated to ascertain the availability of uranium hydride in tonnage quantities.
Date: April 10, 1950
Creator: Kitzes, A. S.
Partner: UNT Libraries Government Documents Department
open access

Investigations of Slot Configurations for Film-Cooled Turbine Blades by Flow Visualization Methods

Description: Memorandum presenting a procedure for obtaining qualitative information on the effectiveness of different slot configurations to make the flow of the cooling air visible. Two methods are utilized: one utilizes the traces caused by a reaction between paint spread over the blade surface and a gas mixed with the cooling air, while the other utilized smoke mixed with the cooling air to make it visible. From the visual observations, the use of a continuous slot as a means of creating the cooling fil… more
Date: October 10, 1950
Creator: Eckert, E. R. G.; Jackson, Thomas W. & Francisco, Allen C.
Partner: UNT Libraries Government Documents Department
open access

Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures

Description: From Summary: "Procedures for applying these analytical methods to experimentally measured blade-metal temperatures are presented. Data are presented for the leading and trailing edge of a symmetrical water-cooled blade to illustrate the validity of the methods for those portions of the blade. In addition to the application to turbine blades, the methods can be applied to any heat-transfer apparatus having a profile that can be approximated by the shape discussed."
Date: April 10, 1950
Creator: Brown, W. Byron & Esgar, Jack B.
Partner: UNT Libraries Government Documents Department
open access

Pressure Measurements on a Sharply Converging Fuselage Afterbody With Jet on and Off at Mach Numbers From 0.8 to 1.6

Description: Report presenting testing of a rocket-powered model of a fin-stabilized parabolic body of revolution with fineness ratio 8.91 and maximum diameter at 80 percent of body station at a range of Mach numbers to determine the static pressures at two orifices on the rearward side of the stabilizing fins. Results regarding measured pressures, comparison of theory and experiment, and drag are provided.
Date: August 10, 1950
Creator: Stoney, William E., Jr. & Katz, Ellis
Partner: UNT Libraries Government Documents Department
open access

Exploratory Investigation of Leading-Edge Chord-Extensions to Improve the Longitudinal Stability Characteristics of Two 52 Degree Sweptback Wings

Description: Report presenting exploratory testing obtained with leading-edge wing chord-extensions on two 52 degree sweptback wings. The wings had the same aspect ratio but different airfoil sections. Results regarding force characteristics and flow characteristics are provided.
Date: March 10, 1950
Creator: Furlong, G. Chester
Partner: UNT Libraries Government Documents Department
open access

Investigation at High Subsonic Speeds of Methods of Alleviating the Adverse Interference at the Root of a Swept-Back Wing

Description: Memorandum presenting an investigation of the interference at the root of a sweptback wing at high subsonic Mach numbers by means of wind-tunnel measurements of a wing-body combination with the 50-percent-chord line of the wing either unswept or swept back 35 degrees. Results regarding body characteristics, pressure studies, tuft studies, and force studies are provided.
Date: August 10, 1950
Creator: Boddy, Lee E.
Partner: UNT Libraries Government Documents Department
open access

Study of flow conditions and deflection angle at exit of two-dimensional cascade of turbine rotor blades at critical and supercritical pressure ratios

Description: Report presenting an analysis of the flow conditions downstream of a cascade of turbine rotor blades at critical and supercritical pressure ratios. Five theoretical methods are compared with an experimental method using the conservation-of-momentum principle and static-pressure surveys as well as schileren photographs of the flow downstream of the blades. Results regarding static-pressure surveys and schileren photographs are provided.
Date: March 10, 1950
Creator: Hauser, Cavour H.; Plohr, Henry W. & Sonder, Gerhard
Partner: UNT Libraries Government Documents Department
open access

Lateral-control investigation of flap-type controls on a wing with upswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Description: Report presenting an investigation using the transonic-bump method through a range of Mach numbers in the high speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls with various spans and spanwise locations. Rolling moments, pitching moments, and lift were obtained through a small range of control deflections.
Date: March 10, 1950
Creator: Hammond, Alexander D.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle

Description: An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowe… more
Date: July 10, 1950
Creator: Grey, Ralph E.; Brightwell, Virginia L. & Barson, Zelmar
Partner: UNT Libraries Government Documents Department
open access

Pressure Measurements at Supersonic Speeds on a Section of a Rectangular Wing Having an NACA 65-009 Profile

Description: Report presenting an investigation of a rectangular wing with a subsonic-type round-leading-edge airfoil section (NACA 65-009) at various Mach numbers. The results generally agreed with calculated values with the exception of the laminar-separated region on the low-pressure surface of the model. Results regarding the calculation of pressure distribution, experimental pressure distributions, aerodynamic characteristics, and shadowgraph studies are provided.
Date: March 10, 1950
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department
open access

Planing Characteristics of Six Surfaces Representative of Hydro-Ski Forms

Description: Report presenting the planing characteristics for six surfaces representative of hydro-ski forms as determined by tank tests.Testing was made at specified trims, speeds, and sufficient loads to define variations with wetted length. Data from the testing is provided in the form of plots of wetted length, load, resistance, trimming moment, and draft against wetted area.
Date: February 10, 1950
Creator: Wadlin, Kenneth L. & McGehee, John R.
Partner: UNT Libraries Government Documents Department
open access

A Transonic-Wing Investigation in the Langley 8-foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-Fuselage Configuration with a Wing of 45 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Description: Memorandum presenting an investigation of a series of wing-fuselage configurations to determine the effects of wing geometry on aerodynamic characteristics. This paper presents the force, moment, wake, and downwash measurements made on a fuselage and wing-fuselage combination of specified measurements. The current phase of the investigation is focused on varying the sweepback of the 0.25-chord line of the wing.
Date: October 10, 1950
Creator: Osborne, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Effect of Mach Number on Over-All Performance of Single-Stage Axial-Flow Compressor Designed for High Pressure Ratio

Description: "A complete stage of an axial-flow compressor designed to produce a high pressure ratio was investigated at speeds from 110 to 130 percent of design speed (836 ft/sec). The data obtained and the results of a previous investigation of the same compressor at speeds from 50 to 100 percent of design speed were used to determine the effect of Mach number on over-all performance. The peak total-pressure ratio increased from 1.095 to 1.515 and the peak adiabatic efficiency decreased from 0.93 to 0.89 … more
Date: July 10, 1950
Creator: Voit, Charles H.; Guentert, Donald C. & Dugan, James F.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Control Characteristics at Mach Numbers of 1.40 and 1.59

Description: Report presenting an investigation to determine the static lateral control characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The aileron effectiveness was about half of what was predicted by calculations, which was mainly due to flow separation in the region of the aileron. Information about other aileron characteristics and characteristics in sideslip is provided.
Date: November 10, 1950
Creator: Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees

Description: Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date: October 10, 1950
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
Partner: UNT Libraries Government Documents Department
open access

The Stability of the Compression Cover of Box Beams Stiffened by Posts

Description: "An investigation is made of the buckling of the compression cover of post-stiffened box beams subjected to end moments. Charts are presented for the determination of the minimum post axial stiffnesses and the corresponding compressive buckling loads required for the compression cover to buckle with nodes through the posts. Application of the charts to design and analysis and the limitations of their use are discussed" (p. 1087).
Date: May 10, 1950
Creator: Seide, Paul & Barrett, Paul F.
Partner: UNT Libraries Government Documents Department
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