44 Matching Results

Search Results

Results: 1 - 24 next
open access

Special Studies in Electrolysis Mitigation: 4. A Preliminary Report on Electrolysis Mitigation in Elyria, Ohio, with Recommendations for Mitigation

Description: Technical paper issued by the Bureau of Standards over surveys conducted on the electrical conditions of railway tracks in Elyria, Ohio. The results of the surveys are presented and discussed. This paper includes tables, maps, and illustrations.
Date: January 22, 1916
Creator: McCollum, Burton & Logan, K. H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the NACA 4-(3)(8)-045 Two-Blade Propellers at Forward Mach Numbers to 0.725 to Determine the Effects of Compressibility and Solidity on Performance

Description: From Summary: "As part of a general investigation of propellers at high forward speeds, tests of two 2-blade propellers having the NACA 4-(3)(8)-03 and NACA 4-(3)(8)-45 blade designs have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.725 to establish in detail the changes in propeller characteristics due to compressibility effects. These propellers differed primarily only in blade solidity,… more
Date: January 22, 1944
Creator: Stack, John; Draley, Eugene C.; Delano, James B. & Feldman, Lewis
Partner: UNT Libraries Government Documents Department
open access

The Digging-in of a Warped Rod Into a Rib

Description: Abstract. Some rather idealized considerations are given regarding the depth a warped rod presses into the ribs at the places of contact. It appears that this distance may, under some conditions, be of the order of 70 times greater than for a straight rod resting uniformly on the ribs.
Date: January 22, 1945
Creator: Martin, A. V.
Partner: UNT Libraries Government Documents Department
open access

Drag Measurements at Transonic Speeds of NACA 65-009 Airfoils Mounted on a Freely Falling Body to Determine the Effects of Sweepback and Aspect Ratio

Description: From Summary: "Drag measurements at transonic speeds on rectangular airfoils and on airfoils swept back 450 are reported. These airfoils, which were mounted on cylindrical test bodies, are part of a series being tested in free drops from high altitude to determine the effect of variation of basic airfoil parameters on airfoil drag characteristics at transonic speeds. These rectangular and swept-back airfoils had the same span, airfoil section (NACA 65-009), and chord perpendicular to the leadin… more
Date: January 22, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department
open access

Effect of Exhaust Pressure on the Cooling Characteristics of a Liquid-Cooled Engine

Description: "Data for a liquid-cooled engine with a displacement volume of 1710 cubic inches were analyzed to determine the effect of exhaust pressure on the engine cooling characteristics. The data covered a range of exhaust pressures from 7 to 62 inches of mercury absolute, inlet-manifold pressures from 30 to 50 inches of mercury absolute, engine speeds from 1600 to 3000 rpm, and fuel-air ratios from 0.063 to 0.100. The effect of exhaust pressure on engine cooling was satisfactorily incorporated in the N… more
Date: January 22, 1947
Creator: Doyle, Ronald B. & Desmon, Leland G.
Partner: UNT Libraries Government Documents Department
open access

Performance of the 19XB 10-Stage Axial-Flow Compressor with Altered Blade Angles

Description: "Previous performance data of the 19XB axial-flow compressor indicated that the outlet guide vanes and possibly the inlet guide vanes were stalling. Calculations were made to determine if these adverse conditions could be eliminated and if the manufacturer's design specifications could be more nearly approached by altering the blade angles of the first few compression stages as well as the outlet guide vanes. With the blade angles altered, experimental data were taken at compressor speeds of 85… more
Date: January 22, 1947
Creator: Downing, Richard M.; Finger, Harold B. & Roepcke, Fay A.
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor of XJ-41-V Turbojet Engine, 4, Performance Analysis Over Range of Compressor Speeds from 5000 to 10,000 RPM

Description: "An investigation of the XJ-41-V turbojet-engine compressor was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the original compressor indicated the compressor would not meet the desired engine-design air-flow requirements because of an air-flow restriction in the vaned collector. The compressor air-flow choking point occurred n… more
Date: January 22, 1948
Creator: Creagh, John W. R. & Ginsburg, Ambrose
Partner: UNT Libraries Government Documents Department
open access

Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. 1: the effect of Reynolds number and Mach number on the aerodynamic characteristics of the wing with flap undeflected

Description: Report presenting testing of a semispan model of a wing of triangular plan form and aspect ratio 2 in the 12-foot pressure tunnel to determine the aerodynamic characteristics of the wing as influenced by the independent effects of Reynolds number and Mach number up to Mach numbers approaching unity. Results regarding the effect of body and effect of wing-profile modification are also provided.
Date: January 22, 1948
Creator: Edwards, George G. & Stephenson, Jack D.
Partner: UNT Libraries Government Documents Department
open access

Dynamic Longitudinal Stability and Control of Tandem Coupled Bomber-Fighter Airplane Models With Rigid and Pitch-Free Couplings

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic longitudinal stability and control characteristics of tandem-coupled bomber-fighter airplane models. Results regarding bomber alone tests, freely coupled combination, and rigidly coupled combination are provided.
Date: January 22, 1951
Creator: Grana, David C. & Hewes, Donald E.
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: Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59

Description: Report presenting an investigation of a supersonic aircraft configuration and various combinations of its components at a range of Mach numbers. Longitudinal- and lateral-force characteristics of the configurations, as well as longitudinal- and lateral-stability derivatives, are provided.
Date: January 22, 1951
Creator: Smith, Norman F. & Marte, Jack E.
Partner: UNT Libraries Government Documents Department
open access

Mercury Amalgam Bonding of Uranium and Copper

Description: Technical report summarizing one phase of work done to develop methods of bonding uranium to a metal which is a good conductor of heat. Silver was chosen for contact with uranium because it is easy to plate on uranium and there is no danger of brittle Ag-U compounds being formed at elevated temperatures. [From Abstract]
Date: January 22, 1951
Creator: Glasgow, L. G.
Partner: UNT Libraries Government Documents Department
open access

Corrosion of Aluminum in Alum Coagulated Process Water

Description: The following report provides the results of an accelerated corrosion test that was performed to compare the effect of two coagulants on the corrosion rates of aluminum slug jacket alloy and 72S. Additionally, some analytical data on the water from the two treatments were obtained and are presented in this report.
Date: January 22, 1952
Creator: Dalrymple, R. S.
Partner: UNT Libraries Government Documents Department
open access

The Crystal Structure of Neptunium Metal

Description: The following report provides measurements of the crystalline structure of neptunium metal.
Date: January 22, 1952
Creator: Zacharissen, W. H.
Partner: UNT Libraries Government Documents Department
open access

Effect of Various Blade Modifications on Performance of a 16-Stage High-Pressure-Ratio Axial-Flow Compressor 1 - Effect on Over-All Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-Blade Angles 3 Degrees

Description: The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.
Date: January 22, 1952
Creator: Medeiros, Arthur A.; Hatch, James E. & Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Method of Estimating the Stick-Fixed Longitudinal Stability of Wing-Fuselage Configurations Having Unswept or Swept Wings

Description: Memorandum presenting a method for calculating the stick-fixed longitudinal stability of a wing-fuselage configuration at subcritical Mach numbers. The method applies to unswept- and swept-wing configurations. The stability parameters estimated by the method show reasonable agreement with the experimental values for the 23 configurations used in the comparison.
Date: January 22, 1952
Creator: McLaughlin, Milton D.
Partner: UNT Libraries Government Documents Department
open access

Summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations at Mach numbers from 0.6 to 1.7 as determined from rocket-powered models

Description: A summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations for use at a range of Mach numbers. The values obtained were determined by the combined use of experimentally determined free-flight data and subsonic aerodynamic theory.
Date: January 22, 1952
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds

Description: Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date: January 22, 1952
Creator: Gracey, William; Pearson, Albin O. & Russell, Walter R.
Partner: UNT Libraries Government Documents Department
open access

The Approximation with Anisotropic Effects for Cylindrical Geometry

Description: The method of spherical harmonic tensors developed Mark for solving the Boltzmann transport equation in isotropic media is herein extended to anisotropic media for cylindrical geometry. A formal solution is given for the case of two concentric cylindrical media, A and B, but no numerical work has yet been done. The following treatment differs from a similar one by the H. K. Ferguson Co. in that the external medium B is assumed to be both a neutron absorber and finite in extent rather than a non… more
Date: January 22, 1953
Creator: Fleck, J.
Partner: UNT Libraries Government Documents Department
open access

Hinge-moment characteristics for several tip controls on a 60 degree sweptback delta wing at Mach number 1.61

Description: Report presenting an investigation at Mach number 1.61 to determine the hinge-moment characteristics of seven tip controls on a 60 degree sweptback delta wing. Testing occurred over a range of angles of attack and control deflection. The results indicated that the most important parameter in designing delta-wing tip control is the ratio of control-surface area ahead of the hinge line to total control-surface area.
Date: January 22, 1953
Creator: Czarnecki, K. R. & Lord, Douglas R.
Partner: UNT Libraries Government Documents Department
open access

In-Line Scintillation Gamma Monitor : Preliminary Specifications

Description: From introduction: "The following recommendations represent the best estimate, based on present knowledge, of the requirements for generally applicable or "universal" instrument for the continuous monitoring of radioactive process streams in terms of their gamma activity."
Date: January 22, 1953
Creator: Upson, U. L. & Connally, R. E.
Partner: UNT Libraries Government Documents Department
open access

Influence of Absorption on the Effective Value of Eta

Description: This report follows calculations performed to determine the effect of epithermal capture on the value of eta to be used in lattice calculations.
Date: January 22, 1953
Creator: Cohen, E. Richard, 1922-
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effect of Chordwise Positioning and Shape of an Underwing Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness-Ratio Wing of Aspect Ratio 6

Description: Report presenting an investigation of three different nacelles in an underwing position at the 0.46 semispan station of a 45 degree sweptback wing at three chordwise positions for a range of Mach numbers. The nacelle profiles were an ogive cylinder, an NACA 65A-series airfoil, and an NACA 0-series airfoil (reversed). Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.
Date: January 22, 1953
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Summary of pitch-damping derivatives of complete airplane and missile configurations as measured in flight at transonic and supersonic speeds

Description: Report presenting longitudinal-damping data in the form of the pitching-moment derivatives and summarized from flight tests of rocket-propelled models and full-scale airplanes. 22 models and 4 airplanes are examined in the study and the damping derivative results are generalized.
Date: January 22, 1953
Creator: Gillis, Clarence L. & Chapman, Rowe, Jr.
Partner: UNT Libraries Government Documents Department
open access

An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: "Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been made at Mach numbers 1.62 and 2.41. Schlieren studies at a Mach number 1.93 for the same five plan-form wings were made to illustrate the behavior of the vortex sheet. The surveys were conducted at 1.5, 3, and 4 root chords behind three triangular wings of 50 degree, 63 degree, and 72 degree leading-edge sweep angle, and behind the 50 degree triangular wing reversed" (p. 1067).
Date: January 22, 1954
Creator: Boatright, William B.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen