Access
Resource Type
Partner
Collection
Congressional Research Service Reports
122
Office of Scientific & Technical Information Technical Reports
120
Technical Report Archive and Image Library
33
National Advisory Committee for Aeronautics Collection
19
Government Accountability Office Reports
16
TRAIL Microcard Collection
10
John F. Kennedy Memorial Collection
2
John F. Kennedy, Dallas Police Department Collection
2
LGBT Collections
2
Texas Stonewall Democratic Caucus Papers (The Dallas Way)
2
3 More
Country
States
Counties
Decade
Month
Day
Language
298 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
298
next
The experimental determination of the moments of inertia of airplanes
The application of the pendulum method to the experimental determination of the moments of inertia of airplanes is discussed in this report. Particular reference is made to the effects of the air, in which the airplane is immersed, on the swinging tests and to the procedure by which these effects are taken into account. This procedure has been used for some time, and the data on several airplanes for which the moments of inertia have been found are included.
Date:
June 8, 1933
Creator:
Soulé, Hartley A. & Miller, Marvel P.
System:
The UNT Digital Library
Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 12: Upper-Surface Ailerons on Wings With Split Flaps
"This report covers the twelfth of a series of tests conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present wind tunnel tests were made with two sizes of upper-surface ailerons on rectangular Clark Y wing models equipped with full span split flaps. The tests showed the effect of the upper-surface ailerons and of the split flaps on the general performance characteristics of the wings, and on the lateral controllability and stability characteristics" (p. 463).
Date:
June 8, 1934
Creator:
Weick, Fred E. & Wenzinger, Carl J.
System:
The UNT Digital Library
Potential flow about arbitrary biplane wing sections
From Summary: "A rigorous treatment is given of the problem of determining the two-dimensional potential flow around arbitrary biplane cellules. The analysis involves the use of elliptic functions and is sufficiently general to include the effects of such elements as the section shapes, the chord ratio, gap, stagger, and decalage, which elements may be specified arbitrarily. The flow problem is resolved by making use of the methods of conformal representation. Thus the solution of the problem of transforming conformally two arbitrary contours into two circles is expressed by a pair of simultaneous integral equations, for which a method of numerical solution is outlined."
Date:
June 8, 1935
Creator:
Garrick, I. E.
System:
The UNT Digital Library
The influence of lateral stability on disturbed motions of an airplane with special reference to the motions produced by gusts
"Distributed lateral motions have been calculated for a hypothetical small airplane with various modifications of fin area and dihedral setting. Special combinations of disturbing factors to simulate gusts are considered and the influence of lateral stability on the motions is discussed. Fin area and wing dihedral were found to be of primary importance in side gusts. It was found that the rolling action of the wing with as much as 5 degrees dihedral was distinctly unfavorable, especially when the weathercock stability was small. It is pointed out that the greatest susceptibility to lateral disturbances lies in the inherent damping and coupling moments developed by the wing" (p. 507).
Date:
June 8, 1938
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Technical Division weekly progress report for period ending June 5, 1943
This report details Technical Division activities for the week ending June 5, 1943.
Date:
June 8, 1943
Creator:
unknown
System:
The UNT Digital Library
The development and application of high-critical-speed nose inlets
From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was undertaken in the Langley 8-foot high-speed tunnel to establish the effects of nose-inlet proportions on critical Mach number to develop a rational method for the design of high-critical-speed nose inlets to meet desired requirements."
Date:
June 8, 1945
Creator:
Baals, Donald D.; Smith, Norman F. & Wright, John B.
System:
The UNT Digital Library
Beta Magnet Current Stability
Abstract: A TEC regulator amplifier driving an Eaterline-Angus recording meter was used to record magnet current variations. Tests were made to determine magnet current variations. Tests were made to determine magnet current stability for currents from 500 amperes to 4000 amperes. Changes were necessary in both the TEC and GE regulators before currents below 2500 amperes could be regulated. Regulation to 0.025 percent for and hour was obtained for currents of 1000 to 4000 amperes with the TEC and GE regulators, and regulation to 0.05 percent for 500 ampere currents.
Date:
June 8, 1947
Creator:
Hudson, E. D. & Becker, M. C.
System:
The UNT Digital Library
Ice protection of turbojet engines by inertia separation of water 2: single-offset-duct system
Investigation of a single-offset-duct system designed to prevent entrance of water into a turbojet engine was conducted on a half-scale nacelle model. An investigation was made to determine ram-pressure recovery and radial velocity profiles at the compressor section and icing characteristics of such a duct system. At a design inlet velocity of 0.77, the maximum ram-pressure recovery attained with effective water-separating inlet was 77 percent, which is considerably less than attainable with a direct-ram inlet. Continuous heating of the accessory-housing surface would be required for inlets that have a small ice storage space.
Date:
June 8, 1948
Creator:
von Glahn, Uwe
System:
The UNT Digital Library
Ice protection of turbojet engines by inertia separation of water 3: annular submerged inlets
Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at inlet-velocity ratio of 0.86. All inlets exhibited considerable screen icing. Severe mass-flow shifts occurred at angles of attack.
Date:
June 8, 1948
Creator:
von Glahn, Uwe
System:
The UNT Digital Library
Internal-Film Cooling of Rocket Nozzles
Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections.
Date:
June 8, 1948
Creator:
Sloop, J. L. & Kinney, George R.
System:
The UNT Digital Library
Investigation of Effects of Several Fuel-Injection Locations on Operational Performance of a 20-Inch Ram Jet
Report presenting the results of an investigation to determine the effects of several methods of fuel injection on the operational performance of a 20-inch ram jet. Four fuel-injection arrangements using the same flame holder were presented. Results regarding the variation of combustion efficiency, ram-pressure ratio, location of the point of fuel injection, and range of fuel-air ratios over which combustion can be maintained are provided.
Date:
June 8, 1948
Creator:
Sterbentz, W. H.; Perchonok, E. & Wilcox, F. A.
System:
The UNT Digital Library
Strategic Objectives - The Ability of Chemically Propelled Aircraft to Complete Missions Against Russian Targets
None
Date:
June 8, 1948
Creator:
Shoults, R. D.
System:
The UNT Digital Library
Estimated transonic flying qualities of a tailless airplane based on a model investigation
Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date:
June 8, 1949
Creator:
Donlan, Charles J. & Kuhn, Richard E.
System:
The UNT Digital Library
Study of sand filter efficiency data
None
Date:
June 8, 1949
Creator:
Healy, W. C. Jr.
System:
The UNT Digital Library
100 Areas technical activities report: Physics, May 1950
This monthly report details the 100 Area technical activities of the Physics Group for the month of May 1950.
Date:
June 8, 1950
Creator:
Gast, P. F.
System:
The UNT Digital Library
The Absorption and Translocation of Several Fission Elements by Russian Thistle
Abstract: An investigation was conducted to determine the absorption and translocation of fission products by Russian thistle from a localized spot of contaminated soil. The amount and identity of the radioactive elements absorbed and translocated by the Russian thistle is given along with the location of these elements in the plants. Beta radioactivity to the amounts of 10 microcuries per gram caused no visible effects on the growth habits of sectioned material are included.
Date:
June 8, 1950
Creator:
Selders, A. A.
System:
The UNT Digital Library
Toxicological Studies of Certain Throium Salts
None
Date:
June 8, 1950
Creator:
Mattis, P.A.
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 3-percent-thick, biconvex section
Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex 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:
June 8, 1951
Creator:
Heitmeyer, John C.
System:
The UNT Digital Library
The Synthetic Liquid Fuel Potential of Missouri
Report documenting the suitability of Missouri for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.
Date:
June 8, 1951
Creator:
Ford, Bacon, and Davis
System:
The UNT Digital Library
The Vapor Pressure and Heat of Vaporization of Bromine Triflouride
The vapor pressure of bromine trifluoride has been measured over the range 39 to 155 C. and the following equation was derived by methods of least squares to represent the experimental data. log{sub 10}P{sub mm} = 7.74853 - l685.8/(t + 220.57). The heat of vaporization was estimated from the following equation which is based upon the Clausius-Clapeyron relation. {Delta}H{sub cal/mole} = 7714 [(t + 273.16)/(t + 220.57)]{sup 2}. In continuation of the program to measure the physical properties of interhalogens, the vapor pressure of bromine trifluoride has been determined. Ruff and Braida (4) measured some of the physical and chemical properties including the vapor pressure over a limited range, 4 to 136 mm. The present investigation extends the vapor pressure data to 2 l/2 atmospheres on material of high purity.
Date:
June 8, 1951
Creator:
G.D., Grisard J.W. and Oliver
System:
The UNT Digital Library
Bibliography : Impact Testing of Materials
The bibliography provided investigates the following sources: Chemical Abstracts 1947-1950., Metallurgical Abstracts Vols. 1-18., ASM Review of Metals Literature Vols. 1-6., J. Institute of Metals Vols. 78-80 (No. 7)., Physics Abstracts 1937-1950.
Date:
June 8, 1952
Creator:
Fick, Jean
System:
The UNT Digital Library
Diffusion factor for estimating losses and limiting blade loadings in axial-flow-compressor blade elements
Report presenting a simplified limiting-blade-loading parameter for axial-flow-compressor blade elements derived from the application of a separation criterion used in two-dimensional boundary-layer theory to a typical suction-surface velocity distribution of a compressor blade element at design angle of attack. Results regarding two-dimensional cascade, compressor rotors, and compressor stators are provided.
Date:
June 8, 1953
Creator:
Lieblein, Seymour; Schwenk, Francis C. & Broderick, Robert L.
System:
The UNT Digital Library
Electrical Resistance Measurements of an Irradiated Uranium Sample
The results of electrical resistance measurements have been used as a means of following changes occurring in metals due to irradiation. The electrical conductivity is sensitive to changes in composition and to cold-work or structure damage. In an anisotropic metal, such as uranium, the director of measurement also influences to some extent the values obtained. For these reasons it is essential to use the same material, and if possible the same piece of material, in comparing the electrical properties before and after irradiation. This report is a description of the measurements made on pieces of the same uranium rod before and after an exposure of approximately 150 MWD/T. The results, while preliminary in nature and dealing only with one sample and exposure level, provide data for which a comparison may be made of the electrical resistivity of irradiated and non-irradiated uranium metal.
Date:
June 8, 1953
Creator:
Kemper, Robert S. & Boyd, C. L.
System:
The UNT Digital Library
An Experimental Investigation of Wheel Spin-Up Drag Loads
Report presenting information on landing gear applied drag loads and the nature of wheel spin-up in landing based on testing in the Langley impact basin. Particular attention is paid to the nature and variation of the coefficient of friction between the tire and runway during the wheel spin-up process. Results regarding the fundamentals of the process, comparison of maximum loads, variation of coefficient of friction, and effect of prerotation are provided.
Date:
June 8, 1953
Creator:
Milwitzky, Benjamin; Lindquist, Dean C. & Potter, Dexter M.
System:
The UNT Digital Library