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Flight investigation of the effect of control centering springs on the apparent spiral stability of a personal-owner airplane

Description: Report presents the results of a flight investigation conducted on a typical high-wing personal-owner airplane to determine the effect of control centering springs on apparent spiral stability. Apparent spiral stability is the term used to describe the spiraling tendencies of an airplane in uncontrolled flight as affected both by the true spiral stability of the perfectly trimmed airplane and by out-of-trim control settings. Centering springs were used in both the aileron and rudder control sys… more
Date: March 22, 1951
Creator: Campbell, John P.; Hunter, Paul A.; Hewes, Donald E. & Whitten, James B.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99

Description: The effects of fineness ratio (14.2 and 12.2) and boattailing on aerodynamic characteristics of four bodies of revolution at Mach numbers from 1.50 to 1.99 within a range of angles of attack from 0 degrees 10 degrees at an approximate Reynolds number of 35x10(superscript)6 based on body length were investigated. A comparison of experimental data with available theory is included. At zero angle of attack, fineness ratio has no appreciable effect on model characteristics while boattailing and boa… more
Date: May 22, 1951
Creator: Cohen, Robert J.
Partner: UNT Libraries Government Documents Department
open access

Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls With Application to Turbine Blade Cooling

Description: "An approximate method for the development of flow and thermal boundary layers in the laminar region on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by the use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout the boundary layer is assumed. The velocity and temperature profiles within the boundary layer are approximated by expressions composed of trigonometric functions"… more
Date: June 22, 1951
Creator: Eckert, E. R. G. & Livingood, J. N. B.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Helmholtz Resonators for Damping Pressure Fluctuations in 3.6-Inch Ram Jet at Mach Number 1.90

Description: Memorandum presenting an investigation conducted at Mach number 1.90 to determine if Helmholtz resonators can be used in a typical ramjet configuration to damp pressure pulsations associated with shock oscillations. Only one of the two resonators was found to effectively damp pressure pulsations that occurred when the ram jet was operating in the vicinity of its peak pressure recovery. Neither was found to effectively damp pressure pulsations over the entire range of ramjet operating conditions. more
Date: May 22, 1951
Creator: Fox, Jerome L.
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

Low-Speed Characteristics of a 45 Degree Sweptback Wing of Aspect Ratio 8 From Pressure Distributions and Force Tests at Reynolds Numbers From 1,500,000 to 4,800,000

Description: Report presenting an investigation of the longitudinal characteristics of a wing with 45 degree sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub)1A012 airfoil sections. The results were obtained from force measurements and distribution measurements for a range of Reynolds numbers. Information regarding lift and pitching-moment characteristics, drag characteristics, and loading characteristics is provided.
Date: October 22, 1951
Creator: Graham, Robert R.
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

The torsional deflections of several propellers under operating conditions

Description: Report presenting propeller-blade torsional-deflection data obtained during an investigation of the pressure distribution on constant-chord solid aluminum-alloy blades differing only in camber and thickness. Testing indicated that thinner blades were able to produce greater amounts of deflection. Results regarding torsional deflections are also provided.
Date: June 22, 1951
Creator: Gray, W. H. & Allis, A. E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Low-Speed Lateral Control and Hinge-Moment Characteristics of a 20-Percent-Chord Plain Aileron on a 47.7 Degrees Sweptback Wing of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)

Description: Report presenting the low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degree sweptback wing of aspect ratio 5.1 in the pressure tunnel. The tests were performed with and without high-lift and stall-control devices. Results regarding the basic aileron data, rolling-moment characteristics, and pitching-moment characteristics are also provided.
Date: October 22, 1951
Creator: Hadaway, William M. & Salmi, Reino J.
Partner: UNT Libraries Government Documents Department
open access

Effects of Reynolds Number on the Aerodynamic Characteristics of a Delta Wing at Mach Number of 2.41

Description: Memorandum presenting the results of an experimental investigation to determine the effects of Reynolds number on the flow characteristics over a delta wing at a Mach number 2.41. The wing streamwise airfoil sections are based on the NACA 00-thickness series with the maximum thickness varying from 4 percent at the root section to 6.24 percent at the 90-percent spanwise station. Results regarding force data and pressure-distribution data are provided.
Date: October 22, 1951
Creator: Hatch, John E., Jr. & Hargrave, L. Keith
Partner: UNT Libraries Government Documents Department
open access

Influence of airfoil trailing-edge angle and trailing-edge-thickness variation on the effectiveness of a plain flap at high subsonic Mach numbers

Description: Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap as determined from wind tunnel tests over a range of Mach numbers. Results regarding the section lift and pitching-moment characteristics, variation of lift coefficient with flap deflection, schileren photographs, and effect of angle of attack are provided.
Date: May 22, 1951
Creator: Hemenover, Albert D. & Graham, Donald J.
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics of aircraft cooling ejectors having short cylindrical shrouds

Description: The factors affecting the performance of ejector suitable for aircraft cooling are investigated theoretically and experimentally. The investigation covers a range of shroud-to-nozzle diameter ratios from 1.1 to 1.6, of shroud lengths from 0.2 to 2.28 nozzle diameters, of secondary-to-primary weight-flow ratios from 0 to 0.12, and of ambient-to-nozzle pressure ratios from 0.7 to 0.06. The results of a simplified theoretical analysis based on each type of flow are in good agreement with those exp… more
Date: May 22, 1951
Creator: Kochendorfer, Fred D. & Rousso, Morris D.
Partner: UNT Libraries Government Documents Department
open access

The effects on the aerodynamic characteristics of reversing the wing of a triangular wing-body combination at transonic speeds as determined by the NACA wing-flow method

Description: Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the effect on aerodynamic characteristics of reversing a triangular wing with a 6-percent-thick biconvex section. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: October 22, 1951
Creator: McKay, James M. & Hall, Albert W.
Partner: UNT Libraries Government Documents Department
open access

Increased process water pressure to 105 buildings

Description: This document discusses increases in water pressure from the 190 Building process pumps which has been contemplated for a range of pressures up to 550 PSIG. The existing process pumps are dual units, consisting of a steam turbine driven primary pump operated: in series with an electric driven secondary pump. The secondary pumps installed in 100-B, D, F, and H Areas were designed for 400 PSIG working pressure, and were given factory hydrostatic tests of 600 PSIG. The 100-DR pumps were given fact… more
Date: February 22, 1951
Creator: Measly, H. F.
Partner: UNT Libraries Government Documents Department
open access

Hanford Works monthly report, December 1950

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of December 1950. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.
Date: January 22, 1951
Creator: Prout, G. R.
Partner: UNT Libraries Government Documents Department
open access

Corrosion Data for Type 347 Stainless Steel Pipe Waste Metal Recovery Process

Description: Introduction: "A limited test progress for the evaluation of type 347 stainless steel pipe which failed the Huey (?) test has been complicated. The tests reported herein were similar in scope to those reported in document number EW-20765, Corrosion Tests on Stainless Steel Plate, Waste Metal Recovery Process. Material tested was obtained on order number EWC-8553, National Tube Company Heat #3X9741. Lots 9789 and 9790."
Date: May 22, 1951
Creator: Sanborn, Kenneth L.
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

Some Effects of Spanwise Aileron Location and Wing Structural Rigidity on the Rolling Effectiveness of 0.3-Chord Flap-Type Ailerons on a Tapered Wing Having 63 Degrees Sweepback at the Leading Edge and Naca 64A005 Airfoil Sections

Description: Report presenting an investigation of some effects of aileron spanwise location and wing structural rigidity on the rolling power of 0.3-chord plain, flap-type ailerons on a wing with a taper ratio of 0.25, an aspect ratio of 3.5, and swept back 63 degrees at the leading edge. Results regarding the aeroelastic effects and aileron span and spanwise location are provided.
Date: June 22, 1951
Creator: Strass, H. Kurt; Fields, E. M. & Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
open access

Investigation of mechanisms of blade failure of forged Hastelloy B and cast Stellite 21 turbine blades in turbojet engine

Description: An investigation was conducted to study the mechanisms of blade failure of forged Hastelloy B and cast Stellite 21. The blades were mounted in a 16-25-6 alloy rotor and subjected to 20-minute cycles consisting of 15 minutes at rated speed and approximately 5 minutes at idle. The first failures of the Hastelloy B and Stellite 21 blades were probably the result of excessive vibratory stresses and occurred after 14.25 and 16.75 hours, respectively. After 28.75 hours of operation, all but 3 of the … more
Date: August 22, 1951
Creator: Yaker, C.; Robards, C. F. & Garrett, F. B.
Partner: UNT Libraries Government Documents Department
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