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Office of Scientific & Technical Information Technical Reports
1,883
Congressional Research Service Reports
1,407
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250
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215
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[Arrest Warrant: W. Johnston]
Warrant issued by the Laredo mayor's office to arrest W. Johnston in response to a complaint by M. Mendiola that he abused, insulted, and drew a gun on her.
Date:
August 12, 1860
Creator:
Laredo (Tex.)
System:
The Portal to Texas History
[Report, July 12, 1868]
Handwritten report describing the sabbath school, its officers, the number of Sabbaths, and other statistical information about the Sabbath school. H. K. Redway was elected secretary of the Sabbath school.
Date:
July 12, 1868
Creator:
Redway, H. K.
System:
The UNT Digital Library
Extra Officers for the Army, Report
This report contains the opinions and recommendations of the Committee on Military Affairs on the proposed Senate bill 2671 authorizing extra officers for the army. In addition, it compiles correspondence from members of the War Department to show their opinions on the legislation.
Date:
March 12, 1908
Creator:
United States. Congress. Senate. Committee on Military Affairs
System:
The UNT Digital Library
Safety of Life on Navigable Waters During Regattas or Marine Parades
Report of the Committee on Commerce detailing the opinions and recommendations of the Committee on the proposed Senate bill 6028 to provide for safety of life on navigable waters during regattas or marine parades. It includes correspondence from the Department of Commerce and Labor on the proposed legislation.
Date:
March 12, 1908
Creator:
United States. Congress. Senate. Committee on Commerce.
System:
The UNT Digital Library
Performance of a 300-horsepower Hispano-Suiza airplane engine
The National Bureau of Standards tested a 300-horsepower Hispano-Suiza engine to determine the characteristic performance of the engine at various altitudes. The engine was operated at the ground, at 25,000 feet, and at intermediate altitudes, both at full loads similar to those that would be imposed upon the engine at various speeds by a propeller whose normal full-load speed was 1,800 r.p.m. Friction horsepower also was determined in order that the mechanical efficiency of the engine might be calculated.
Date:
May 12, 1920
Creator:
Sparrow, S. W. & White, H. S.
System:
The UNT Digital Library
Voles of the Genus Phenacomys
Nests, young, food, habits, and enemies of the voles of the genus Phenacomys.
Date:
October 12, 1926
Creator:
Howell, A. Brazier
System:
The UNT Digital Library
Report on the Completion of Garza Dam
Report describing the construction and completion of Garza Dam in Dallas County, Texas, resulting in the creation of Lake Dallas. It includes pages of inserted photographs and a fold-out technical drawing that shows a "Typical Section of Completed Fill Between Stas. 15 & 30."
Date:
November 12, 1927
Creator:
Hawley, John B. & Floyd, O. N.
System:
The Portal to Texas History
Speed and deceleration trials of U.S.S. Los Angeles
From Summary: "The trials reported in this report were instigated by the Bureau of Aeronautics of the Navy Department for the purpose of determining accurately the speed and resistance of the U. S. S. "Los Angeles" with and without water recovery apparatus, and to clear up the apparent discrepancies between the speed attained in service and in the original trials in Germany. The trials proved very conclusively that the water recovery apparatus increases the resistance about 20 per cent, which is serious, and shows the importance of developing a type of recovery having less resistance. Between the American and the German speed trials without water recovery there remains an unexplained discrepancy of nearly 6 per cent in speed at a given rate of engine revolutions."
Date:
June 12, 1928
Creator:
De France, S. J. & Burgess, C. P.
System:
The UNT Digital Library
Full-Scale Wind-Tunnel Tests With a Series of Propellers of Different Diameters on a Single Fuselage
"Aerodynamic tests were made with four geometrically similar metal propellers of different diameters, on a Wright "Whirlwind" J-5 engine in an open cockpit fuselage. The results show little difference in the characteristics of the various propellers, the only one of any importance being an increase of efficiency of the order of 1 per cent for a 5 per cent increase of diameter, within the range of the tests" (p. 107).
Date:
March 12, 1929
Creator:
Weick, Fred E.
System:
The UNT Digital Library
Maneuverability investigation of an F6C-4 fighting airplane
"In order to compare the relative maneuverability of two fighting airplanes and to accumulate additional data to assist in establishing a satisfactory criterion for the maneuverability of any airplane, the National Advisory Committee for Aeronautics has conducted maneuverability investigations on the F6C-3 (water-cooled engine) and the F6C-4 (air-cooled engine) airplanes. The investigation made on the F6C-3 airplane was reported in NACA-TR-369. This report contains the results of the investigation made on the F6C-4 airplane" (p. 475).
Date:
December 12, 1930
Creator:
Dearborn, C. H. & Kirschbaum, H. W.
System:
The UNT Digital Library
Ice Prevention on Aircraft by Means of Engine Exhaust Heat and a Technical Study of Heat Transmission From a Clark Y Airfoil
"This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both in the laboratory and in flight show conclusively that it is necessary to heat only the front portion of the wing surface to effect complete prevention" (p. 3).
Date:
June 12, 1931
Creator:
Theodorsen, Theodore & Clay, William C.
System:
The UNT Digital Library
Tests of nacelle-propeller combinations in various positions with reference to wings 2: thick wing - various radial-engine cowlings - tractor propeller
This report is the second of a series giving the results obtained in the 20-foot wind tunnel of the National Advisory Committee for Aeronautics on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. The first report gave the results of the test of a N.A.C.A. cowled air-cooled engine nacelle located in 21 positions with reference to a thick wing. The present report gives results of tests of a normal engine nacelle with several types of cowling and fairings in four of the positions with reference to the same wing. (author).
Date:
May 12, 1932
Creator:
Wood, Donald H.
System:
The UNT Digital Library
Wind-tunnel research comparing lateral control devices, particularly at high angles of attack 6: skewed ailerons on rectangular wings
"This report covers the sixth of a series of investigations in which various lateral control devices are compared with particular reference to their effectiveness at high angles of attack. The present report deals with flap-type ailerons hinged about axes having an angle with respect to the leading and trailing edges of the wing. Tests were made on four different skewed ailerons, including two different angles of skew and two sizes of ailerons" (p. 81).
Date:
July 12, 1932
Creator:
Weick, Fred E. & Harris, Thomas A.
System:
The UNT Digital Library
Annual Report of the Boy Scouts of America: 1933
Annual report submitted by the Boy Scouts of America to Congress describing highlights from 1933, activities, service, public relations, organizational leadership, and other information about scouting programs.
Date:
April 12, 1934
Creator:
Boy Scouts of America
System:
The Portal to Texas History
Full-scale wind-tunnel tests of a PCA-2 autogiro rotor
This report presents the results of force tests on and air-flow surveys near PCA-2 autogiro rotor in the NACA full-scale wind tunnel. The force tests were made at three pitch settings and several rotor speeds; the effect of fairing protuberances on the rotor blade was determined. Induced downwash and yaw angles were determined at low tip-speed ratios in a plane 1 1/2 feet above the path of the blade tips. The results show that the maximum l/d of the rotor cannot be appreciably increased by increasing the blade pitch angle above about 4.5 degrees at the blade tip; that the protuberances on the blades cause more than 5 percent of the total rotor drag; and that the rotor center-of-pressure travel is very small.
Date:
October 12, 1934
Creator:
Wheatley, John B. & Hood, Manley J.
System:
The UNT Digital Library
Potential Flow About Elongated Bodies of Revolution
"This report presents a method of solving the problem of axial and transverse potential flows around arbitrary elongated bodies of revolution. The solutions of Laplace's equation for the velocity potentials of the axial and transverse flows, the system of coordinates being an elliptic one in a meridian plane, are given. The theory is applied to a body of revolution obtained from a symmetrical Joukowsky profile, a shape resembling an airship hull" (p. 189).
Date:
November 12, 1934
Creator:
Kaplan, Carl
System:
The UNT Digital Library
A Flight Investigation of the Spinning of the F4B-2 Biplane with Various Loads and Tail Surfaces
"A flight investigation of the spinning of the F4B-2 single-seat fighter airplane was made for the purpose of finding modifications that would eliminate dangerous spin tendencies exhibited by this type of airplane in service. The effects on steady spins and on recoveries of changing the loading, enlarging the fin areas, changing the elevator plan form, and raising the horizontal surfaces, were determined" (p. 413).
Date:
February 12, 1935
Creator:
Scudder, N. F. & Seidman, Oscar
System:
The UNT Digital Library
Tests of a Wing-Nacelle-Propeller Combination at Several Pitch Settings Up to 42 Degrees
This report presents the results of tests of a 4-foot model of Navy propeller No. 4412 in conjunction with an NACA cowled nacelle mounted ahead of a thick wing in the 20-foot propeller-research tunnel. A range of propeller pitches from 17 degrees to 42 degrees at 0.75r was covered, and for this propeller the efficiency reached a maximum at a pitch setting of 27 degrees; at high pitches the efficiencies were slightly lower. The corrected propulsive efficiency is shown to be independent of the angle of attack for the high-speed and the climbing ranges of flight.
Date:
November 12, 1935
Creator:
Windler, Ray
System:
The UNT Digital Library
Interference of Wing and Fuselage From Tests of 28 Combinations in the N.A.C.A. Variable-Density Tunnel
Report presents the results of tests conducted on 28 wing-fuselage combinations made in the variable-density wind tunnel as a part of the wing-fuselage interference program being conducted therein and in addition to the 209 combinations previously reported in NACA-TR-540. These tests practically complete the study of combinations with a rectangular fuselage and continue the study of combinations with a round fuselage and a tapered wing.
Date:
March 12, 1936
Creator:
Sherman, Albert
System:
The UNT Digital Library
Strength of Welded Aircraft Joints
"This investigation is a continuation of work started in 1928 and described in NACA-TR-348 which shows that the insertion of gusset plates was the most satisfactory way of strengthening a joint. Additional tests of the present series show that joints of this type could be improved by cutting out the portion of the plate between the intersecting tubes. T and lattice joints in thin-walled tubing 1 1/2 by 0.020 inch have somewhat lower strengths than joints in tubing of greater wall thickness because of failure by local buckling. In welding the thin-walled tubing, the recently developed "carburizing flux" process was found to be the only method capable of producing joints free from cracks" (p. 177).
Date:
August 12, 1936
Creator:
Brueggeman, W. C.
System:
The UNT Digital Library
A study of the two-control operation of an airplane
The two-control operation of a conventional airplane is treated by means of the theory of disturbed motions. The consequences of this method of control are studied with regard to the stability of the airplane in its unconstrained components of motion and the movements set up during turn maneuvers.
Date:
August 12, 1936
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Wind-tunnel investigation of wings with ordinary ailerons and full-span external-airfoil flaps
Report presents an investigation carried out in the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil equipped, first, with a full-span NACA 23012 external-airfoil flap having a chord 0.20 of the main airfoil chord and with a full-span aileron with a chord 0.12 of the main airfoil chord on the trailing edge of the main airfoil and equipped second, with a 0.30-chord full-span NACA 23012 external-airfoil flap and a 0.13-chord full-span aileron. The results are arranged in three groups, the first two of which deal with the airfoil characteristics of the two airfoil-flap combinations and with the internal-control characteristics of the airfoil-flap-aileron combinations. The third group of tests deals with several means for balancing ailerons mounted on a special large-chord NACA 23012 external-airfoil flap. The tests included an ordinary aileron, a curtained-nose balance, a frise balance, and a tab.
Date:
March 12, 1937
Creator:
Platt, Robert C. & Shortal, Joseph A.
System:
The UNT Digital Library
A Study of Transparent Plastics for use on Aircraft, Special Report
"Various transparent organic plastics, including both commercially available and experimental materials, have been examined to determine their suitability for use as flexible windshields on aircraft, The properties which have been studied include light transmission, haziness, distortion, resistance to weathering, scratch and indentation hardness, impact strength, dimensional stability, resistance to water and various cleaning fluids, bursting strength at normal and low temperatures, and flammability" (p. 1).
Date:
May 12, 1937
Creator:
Axilrod, Benjamin M. & Kline, Gordon M.
System:
The UNT Digital Library
Wind-Tunnel Investigation of an NACA 23012 Airfoil with Various Arrangements of Slotted Flaps
"An investigation was made in the 7 by 10-foot wind tunnel and in the variable-density wind tunnel of the NACA 23012 airfoil with various slotted-flap arrangements. The purpose of the investigation in the 7 by 10-foot wind tunnel was to determine the airfoil section aerodynamic characteristics as affected by flap shape, slot shape, and flap location. The flap position for maximum lift; polars for arrangements favorable for take-off and climb; and complete lift, drag, and pitching-moment characteristics for selected optimum arrangements were determined" (p. 1).
Date:
February 12, 1938
Creator:
Wenzinger, Carl J. & Harris, Thomas A.
System:
The UNT Digital Library