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Effects of boundary-layer control on the longitudinal characteristics of a 45 degrees swept-forward wing-fuselage combination
Report presenting an investigation to determine the benefits obtainable by applying boundary-layer control to a 45 degree swept-forward wing-fuselage combination. Force and pressure-distribution data were obtained with and without boundary-layer control with various combinations of leading-edge and trailing-edge flaps.
Date:
February 2, 1950
Creator:
McCormack, Gerald M. & Cook, Woodrow L.
Object Type:
Report
System:
The UNT Digital Library
Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body
Report presenting the aerodynamic characteristics of an all-movable, triangular-plan-form wing alone and with a body as determined from semispan model tests. The agreement between calculated and experimental results was not satisfactory for the most part, which seemed to be due to the failure of linear theory to define the actual flow field about the configurations investigated. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date:
February 2, 1950
Creator:
Stivers, Louis S. & Malick, Alexander W.
Object Type:
Report
System:
The UNT Digital Library
Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic bump method
Report presenting an investigation by 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 of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Date:
March 2, 1950
Creator:
Vogler, Raymond D.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds
From Introduction: "An investigation of the high-speed aerodynamic characteristics of a modified delta wing in combination with a fuselage was conducted in the Langley high-speed 7- by 10-foot tunnel. The model was tested on the sting support system through a Mach number range of 0.40 to 0.90 with both free and fixed transition. Because of the nature of the transition effect, the results seemed to be of the general interest and are presented in the present paper."
Date:
May 2, 1950
Creator:
Polhamus, Edward C. & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Ditching Investigation of a 1/24-Scale Model of the Boeing B-47 Airplane
"An investigation of a 1/24-scale dynamically similar model of the Boeing B-47 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves" (p. 1).
Date:
May 2, 1950
Creator:
Fisher, Lloyd J. & Windham, John O.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Effect of Thickening the Aileron Trailing Edge on Control Effectiveness for Sweptback Tapered Wings Having Sharp-and Round-Nose Sections
Report discussing an investigation of the rolling effectiveness at transonic and supersonic speeds on a 38.1 degree sweptback tapered wing with NACA 0010-64 airfoil sections and partial-span ailerons of true contour with a modified flt-side blunt trailing-edge shape. The variation of Reynolds number with Mach number and the control effectiveness is provided.
Date:
May 2, 1950
Creator:
Strass, H. Kurt & Fields, Edison M.
Object Type:
Report
System:
The UNT Digital Library
Hydrofluorination of Zirconium Oxide
This report analyzes experiments on the production of zirconium tetrafluoride and discusses the reactivity data taken after various methods.
Date:
August 2, 1950
Creator:
Phillips, Don
Object Type:
Report
System:
The UNT Digital Library
Preliminary analysis of effects of air cooling turbine blades on turbojet-engine performance
The effects of turbine-blade cooling on engine performance were analytically investigated for a turbojet engine in which cooling air is bled from the engine compressor. The analysis was made for a constant turbine-inlet temperature and a range of altitudes to determine the minimum cooling requirements to permit substitution of nonstrategic materials in turbine blading. The results indicate that, for a constant inlet temperature, air cooling of the turbine blades increases the specific fuel consumption and decreases the thrust of the engine. The highest possible cooling effectiveness is desirable to minimize coolant weight flow and its effects on engine performance.
Date:
August 2, 1950
Creator:
Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine 3: Methods for Determining Power and Efficiency
Suggested formula are given for determining air-cooled turbine-performance characteristics, such as power and efficiency, as functions of certain parameters. These functions, generally being unknown, are determined from experimental data obtained from specific investigations. Special plotting methods for isolating the effect of each parameter are outlined.
Date:
August 2, 1950
Creator:
Ellerbrock, Herman H., Jr. & Ziemer, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Free-Jet Investigation of a 16-Inch Ram Jet at Mach Numbers of 1.35, 1.50, and 1.73
Memorandum presenting the results of a free-jet investigation to determine the internal performance of a 16-inch ram jet. Data were obtained at a range of altitudes and Mach numbers. Results regarding the rake flame holder, effect of fuel injector on burner performance, effect of propylene oxide on burner performance, serrated annular baffle flame holder, diffuser performance, and performance at off-design spike location are provided.
Date:
October 2, 1950
Creator:
Wilcox, Fred; Baker, Sol & Perchonok, Eugene
Object Type:
Report
System:
The UNT Digital Library
Correlation of forced-convection heat-transfer data for air flowing in smooth platinum tube with long-approach entrance at high surface and inlet-air temperatures
A heat-transfer investigation was conducted with air in an electrically heated platinum tube with long-approach entrance, inside diameter of 0.525 inch, and effective heat-transfer length of 24 inches over ranges of Reynolds number up to 320,000, average inside-tube-wall temperature up to 3053 degrees R, and inlet-air temperature up to 1165 degrees R. Correlation of data by the conventional Nusselt relation resulted in separation of data with tube-wall temperature. Good correlation was obtained, however, by use of a modified Reynolds number.
Date:
November 2, 1950
Creator:
Desmon, Leland G. & Sams, Eldon W.
Object Type:
Report
System:
The UNT Digital Library
Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap
Report presenting an investigation at supersonic speeds of some of the factors affecting the flow over a rectangular wing with a symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. The main purpose is to obtain more information on which to base the design of supersonic controls. Results regarding the effect of Mach number, effect of wing thickness, effect of fixing transition, effect of sealing the hinge gap, effect of model surface condition and asymmetry, and shock boundary-layer interaction are provided.
Date:
January 2, 1951
Creator:
Czarnecki, K. R. & Mueller, James N.
Object Type:
Report
System:
The UNT Digital Library
Viscosity and Settling Rates of TBP Waste Metal Slurries as a Function of Shear
This report follows work that is meant to determine the settling rate and viscosity of Hanford Waste metal slurry as a function of prolonged agitation and shear, and to repeat these determinations on a synthetic incubated material similar to that used in the acidification studies, HW-18367, and to make a direct comparison between the genuine and simulated wastes.
Date:
January 2, 1951
Creator:
Varga, L. P. & Harmon, M. K.
Object Type:
Report
System:
The UNT Digital Library
An investigation of convergent-divergent diffusers at Mach number 1.85
Report presenting an investigation in the supersonic tunnel at Mach number 1.85 and angles of attack from 0 to 5 degrees to determine optimum design configurations for a convergent-divergent type of supersonic diffusers with a subsonic diffuser of 5 degrees included divergence angle. Total-pressure recoveries in excess of the theoretical recovery across a normal shock at a free-stream Mach number of 1.85 were obtained with a number of configurations.
Date:
February 2, 1951
Creator:
Wyatt, DeMarquis D. & Hunczak, Henry R.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 2 with NACA 0003-63 section
Report presenting testing of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 2, 1951
Creator:
Heitmeyer, John C. & Smith, Willard G.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with NACA 0005-63 section
Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and NACA 0005-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 2, 1951
Creator:
Heitmeyer, John C. & Stephenson, Jack D.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution, cambered and twisted for trapezoidal span load distribution
"A wing-body combination having a triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution in streamwise planes, and cambered and twisted for a trapezoidal span distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.25 to 0.96 and 1.20 to 1.70 at a Reynolds number of 1.5 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers" (p. 1).
Date:
February 2, 1951
Creator:
Phelps, E. Ray & Smith, Willard G.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of effects of design changes on performance of large-capacity centrifugal compressors
Report presenting an investigation to determine the effects of several design changes on the performance of large-capacity, double-entry, centrifugal compressors. Four modifications of a turbojet engine compressor were operated over a range of equivalent impeller tip speeds an the compressor overall and component performances were determined. Results regarding the impeller performance, diffuser performance, and compressor performance are provided.
Date:
March 2, 1951
Creator:
Withee, Joseph R., Jr.; Kovach, Karl & Ginsburg, Ambrose
Object Type:
Report
System:
The UNT Digital Library
Investigation at zero angle of attack of a 16-inch ram jet engine in 8- by 6-foot supersonic wind tunnel
Report presenting a study in the 8- by 6-foot supersonic wind tunnel of the performance of a 16-inch ramjet engine at zero angle of attack and over a range of free-stream Mach numbers between 1.5 and 2.0. Results regarding diffuser performance, drag evaluation, engine evaluation, and burner performance are provided.
Date:
March 2, 1951
Creator:
Nussdorfer, T.; Wilcox, F. & Perchonok, E.
Object Type:
Report
System:
The UNT Digital Library
Some properties of beryllium oxide and beryllium oxide - columbium ceramals
High-temperature tensile and thermal-shock investigations were conducted on beryllium oxide and beryllium oxide plus columbium metal additions. X-ray diffraction and metallographic results are given. The tensile strength of 6150 pounds per square inch for beryllium oxide at 1800 degrees F compared favorably with the zirconia bodies previously tested. Additions of 2, 5, 8, 10, 12, and 15 percent by weight of columbium metal failed to improve the shock resistance over that of pure beryllium oxide.
Date:
March 2, 1951
Creator:
Robards, C. F. & Gangler, J. J.
Object Type:
Report
System:
The UNT Digital Library
Thermal Conductivity of 14 Metals and Alloys Up to 1100 Degrees Fahrenheit
Memorandum presenting a determination of the thermal conductivity of 14 metals and alloys in temperatures ranges with a maximum of 1100 degrees Fahrenheit. Some of the metals included steels, high-temperature alloys, molybdenum disilicide, aluminum alloys, brass, and silver. A comparison method was used to obtain the results in which the thermal conductivity of the test sample was compared with the conductivity of high-purity lead.
Date:
March 2, 1951
Creator:
Evans, Jerry E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Altitude Operation of Gas-Turbine Engine With Variable-Area Fuel-Nozzle System
From Introduction: "The investigation reported herein was therefore undertaken to extend this study to altitude conditions in which the low fuel-flow rates occur over the full range of engine speeds."
Date:
April 2, 1951
Creator:
Gold, H. & Rosenzweig, S.
Object Type:
Report
System:
The UNT Digital Library
The Solubility of Tributyl Phosphate in Aqueous Solutions
Report describing a study regarding the solubility and related properties of tributyl phosphate (TBP), which has lower solubility in water than most uranium solvents. Pure TBP and TBP in an inert diluent were tested for solubility in water, several nitric acid solutions of varying concentrations, and other solutions typical of process streams. For TBP-diluent-water system tests, equilibrium water content in organic phase was found.
Date:
April 2, 1951
Creator:
Burger, Leland L. & Forsman, R. C.
Object Type:
Report
System:
The UNT Digital Library
The Synthetic Liquid Fuel Potential of Virginia
Report documenting the suitability of Virginia for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.
Date:
April 2, 1951
Creator:
Ford, Bacon, and Davis
Object Type:
Report
System:
The UNT Digital Library