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Congressional Research Service Reports
1,468
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1,461
Technical Report Archive and Image Library
346
Government Accountability Office Reports
194
National Advisory Committee for Aeronautics Collection
191
TRAIL Microcard Collection
121
Texas State Publications
29
Harris and Eliza Kempner
19
John F. Kennedy Memorial Collection
13
John F. Kennedy, Dallas Police Department Collection
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Descriptions of Twenty-six New Species of North American Mammals
Brief description of new species of ground squirrels, Evotomys, Marten, Molossus, prairie dog, kangaroo rats, pocket gopher, and Hesperomys.
Date:
October 8, 1890
Creator:
Merriam, C. Hart
System:
The UNT Digital Library
Revision of the Jumping Mice of the Genus Zapus
Revision of genus Zapus based upon a study of more than 900 specimens, including nomenclature and skull and teeth figures.
Date:
August 8, 1899
Creator:
Preble, Edward A.
System:
The UNT Digital Library
Temperature Measurements in Bessemer and Open-Hearth Practice
Technical paper issued by the Bureau of Standards over studies conducted on different types of furnaces, specifically the Bessemer and the open-hearth furnace. The results of the studies are presented and discussed. This paper includes tables, and illustrations.
Date:
May 8, 1917
Creator:
Burgess, George K.
System:
The UNT Digital Library
Report on the Oil and Gas Possibilities of the University Block 46 in Culberson County
Report that discusses the oil and gas possibilities in Culberson County, Texas. The geology of the area is discussed and divided into two sections.
Date:
December 8, 1923
Creator:
Beede, J. W., 1871-1940
System:
The UNT Digital Library
Characteristics of Five Propellers in Flight
"This investigation was made for the purpose of determining the characteristics of five full-scale propellers in flight. The equipment consisted of five propellers in conjunction with a VE-7 airplane and a Wright E-2 engine. The propellers were of the same diameter and aspect ratio. Four of them differed uniformly in thickness and pitch and the fifth propeller was identical with one of the other four with exception of a change of the airfoil section" (p. 267).
Date:
November 8, 1927
Creator:
Crowley, J. W., Jr. & Mixson, R. E.
System:
The UNT Digital Library
The measurement of fluctuations of air speed by the hot-wire anemometer
"The hot-wire anemometer suggests itself as a promising method for measuring the fluctuating air velocities found in turbulent flow. The only obstacle is the presence of a lag due to the limited energy input which makes even a fairly small wire incapable of following rapid fluctuations with accuracy. This paper gives the theory of the lag and describes an experimental arrangement for compensating for the lag for frequencies up to 100 or more per second when the amplitude of the fluctuation is not too great. An experimental test of the accuracy of compensation and some results obtained with the apparatus in a wind-tunnel air stream are described. While the apparatus is very bulky in its present form, it is believed possible to develop a more portable arrangement" (p. 359).
Date:
January 8, 1929
Creator:
Dryden, H. L. & Kuethe, A. M.
System:
The UNT Digital Library
The Design of Airplane Wing Ribs
"The purpose of this investigation was to obtain information for use in the design of truss and plywood forms, particularly with reference to wing ribs. Tests were made on many designs of wing ribs, comparing different types in various sizes. Many tests were also made on parallel-chord specimens of truss and plywood forms in place of the actual ribs and on parts of wing ribs, such as truss diagonals and sections of cap strips" (p. 223).
Date:
January 8, 1930
Creator:
Newlin, J. A. & Trayer, George W.
System:
The UNT Digital Library
Annual Report of the Boy Scouts of America: 1929
Annual report submitted by the Boy Scouts of America to Congress describing highlights from 1929, activities, department reports, finance, foreign relations, organizational leadership, and other information about scouting programs.
Date:
April 8, 1930
Creator:
Boy Scouts of America
System:
The Portal to Texas History
Comparison of full-scale propellers having R.A.F.-6 and Clark Y airfoil sections
In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the propellers with R. A. F.-6 sections gave about the same maximum efficiency as the Clark Y propellers and were more efficient for the conditions of climb and take-off.
Date:
October 8, 1930
Creator:
Freeman, Hugh B.
System:
The UNT Digital Library
Static, Drop, and Flight Tests on Musselman Type Airwheels
The purpose of this investigation was to obtain quantitative information on the shock-reducing and energy-dissipating qualities of a set of 30 by 13-6 Musselman type airwheels. The investigation consisted of static, drop, and flight tests. The static tests were made with inflation pressures of approximately 0, 5, 10, 15, 20, and 25 pounds per square inch and loadings up to 9,600 pounds.
Date:
October 8, 1930
Creator:
Peck, William C. & Beard, Albert P.
System:
The UNT Digital Library
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
Interference of wing and fuselage from tests of 209 combinations in the NACA variable-density tunnel
This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA variable-density wind tunnel to provide information regarding the effects of aerodynamic interference between wings and fuselages at a large value of Reynolds number.
Date:
March 8, 1935
Creator:
Jacobs, Eastman N. & Ward, Kenneth E.
System:
The UNT Digital Library
A Turbulence Indicator Utilizing the Diffusion of Heat
This report describes a method of determining the turbulence in wind tunnels. The effect of turbulence upon the diffusion of heat from a small electrically heated wire in an air stream was investigated. The turbulence of the stream was introduced by a series of geometrically similar screens placed one at a time across the upstream section of the tunnel. With the wire set at various distances from the screens, curves of temperature distribution were obtained by traversing the heated wake at a distance of 2 inches behind the wire with a small thermocouple.
Date:
March 8, 1935
Creator:
Schubauer, G. B.
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
Measurements of fuel distribution within sprays for fuel-injection engines
Two methods were used to measure fuel distribution within sprays from several types of fuel-injection nozzles. A small tube inserted through the wall of an air tight chamber into which the sprays were injected could be moved about inside the chamber. When the pressure was raised to obtain air densities of 6 and 14 atmospheres, some air was forced through the tube and the fuel that was carried with it was separated by absorbent cotton and weighed. Cross sections of sprays from plain, pintle, multiple-orifice, impinging-jets, centrifugal, lip, slit, and annular-orifice nozzles were investigated, at distances of 1, 3, 5, and 7 inches from the nozzles.
Date:
April 8, 1936
Creator:
Lee, Dana W.
System:
The UNT Digital Library
Pressure-distribution measurements on O-2H airplane in flight
"Results are given of pressure-distribution measurements made over two different horizontal tail surfaces and the right wing cellule, including the slipstream area, of an observation-type biplane. Measurements were also taken of air speed, control-surface positions, control-stick forces, angular velocities, and accelerations during various abrupt maneuvers. These maneuvers consisted of push-downs and pull-ups from level flight, dive pull-outs, and aileron rolls with various thrust conditions" (p. 319).
Date:
December 8, 1936
Creator:
Pearson, H. A.
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
Flow coefficients of monosleeve valves
The flow coefficients of the intake and the exhaust ports of a sleeve-valve cylinder were measured by attaching the cylinder to a large tank and measuring the changes in pressure and temperature in the tank that were caused by short periods of air flow through the valve ports. The derivation of the equations on which the flow coefficients are based is given. The distribution of total pressure in the arms of the sleeve-valve intake manifold was measured. The arms are found to have as little as 75 percent of the total pressure within the manifold entrance.
Date:
February 8, 1940
Creator:
Waldron, C. D.
System:
The UNT Digital Library
Determination of ground effect from tests of a glider in towed flight
Report presents the results of an investigation made to find the effect of ground on the aerodynamic characteristics of a Franklin PS-2 glider. The lift, the drag, and the angle of attack of the glider in towed flight were determined at several heights from 0.14 to 1.19 span lengths and at various speeds for each height. Two wing arrangements were tested: the plain wing, and the wing with a nearly full-span 30-percent-chord split flap deflected 45 degrees. The experimental results for the plain wing were in good agreement with theoretical values calculated by the method of Wieselsberger for both the angle of attack and the drag coefficient at a height of 0.21 span length; Tani's refinements of the theory had a practically negligible effect on the computed values in this case.
Date:
April 8, 1940
Creator:
Wetmore, J. W. & Turner, L. I., Jr.
System:
The UNT Digital Library
Wind-tunnel investigation of effect of interference on lateral-stability characteristics of four NACA 23012 wings, an elliptical and a circular fuselage and vertical fins
Report presents the results of a wind-tunnel investigation of the effect of wing-fuselage interference on lateral-stability characteristics made in the NACA 7 by 10-foot wind tunnel on four fuselages and two fins, representing high-wing, low-wing, and midwing monoplanes. The fuselages are of circular and elliptical cross section. The wings have rounded tips and, in plan form, one is rectangular and the three are tapered 3:1 with various amounts of sweep. The rate of change in the coefficients of rolling moment, yawing moment, and lateral force with angle of yaw is given in a form to show the increment caused by wing-fuselage interference for the model with no fin and the effect of wing-fuselage interference on fin effectiveness. Results for the fuselage-fin combination and the wing tested alone are also given.
Date:
August 8, 1940
Creator:
House, Rufus O. & Wallace, Arthur R.
System:
The UNT Digital Library
Critical Compressive Stress for Flat Rectangular Plates Supported Along All Edges and Elastically Restrained Against Rotation along the Unloaded Edges
A chart is presented for the values of the coefficient in the formula for the critical compressive stress at which buckling may be expected to occur in flat rectangular plates supported along all edges and, in addition, elastically restrained against rotation along the unloaded edges. The mathematical derivations of the formulas required in the construction of the chart are given.
Date:
March 8, 1941
Creator:
Lundquist, Eugene E. & Stowell, Elbridge Z.
System:
The UNT Digital Library
On the Use of Residue Theory for Treating the Subsonic Flow of a Compressible Fluid
"A new mathematical technique, due to Milne-Thomson, is used to obtain an improved form of the method of Poggi for calculating the effect of compressibility on the subsonic flow past an obstacle. By means of this new method, the difficult surface integrals of the original Poggi method can be replaced by line integrals. These line integrals are then solved by the use of residue theory. In this way an equation is obtained giving the second-order effect of compressibility on the velocity of the fluid" (p. 39).
Date:
September 8, 1941
Creator:
Kaplan, Carl
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