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Effect of Rate of Temperature Change on the Transformations in an Alloy Steel
Scientific paper issued by the Bureau of Standards over studies conducted on the effects of temperature change on alloy steel. The experimental methods used and the results are presented and discussed. This paper includes tables, photographs, and illustrations.
Date:
July 10, 1919
Creator:
Scott, Howard
System:
The UNT Digital Library
Strain Lines Developed by Compressive Tests on Structural Members of the Delaware River Bridge at the United States Bureau of Standards for the Delaware River Bridge Joint Commission
Strain lines illustrations from Delaware River Bridge.
Date:
March 10, 1926
Creator:
United States. Bureau of Standards.
System:
The UNT Digital Library
Effect of variation of chord and span of ailerons on rolling and yawing moments in level flight
This report presents the results of an investigation of the rolling and yawing moments due to ailerons of various chords and spans on two airfoils having the Clark Y and U. S. A. 27 wing sections. Some attention is devoted to a study of the effect of scale on rolling and yawing moments and to the effect of slightly rounding the wing tips. The results apply to level flight with the wing chord set at an angle of attack of +4 degrees and to conditions of zero pitch, zero yaw, and zero roll of the airplane. It is planned later to extend the investigation to other attitudes for monoplane and biplane combinations. The work was conducted in the 10 foot wind tunnel of the Bureau of Standards on models of 60-inch span and 10-inch chord. (author).
Date:
July 10, 1928
Creator:
Heald, R. H. & Strother, D. H.
System:
The UNT Digital Library
Full-scale wind-tunnel tests of a propeller with the diameter changed by cutting off the blade tips
Tests were conducted in order to determine how the characteristics of a propeller are affected by cutting off the tips. The diameter of a standard 10-foot metal propeller was changed successively to 9 feet 6 inches, 9 feet 0 inches, 8 feet 6 inches, and 8 feet 0 inches. Each propeller thus formed was tested at four pitch settings using an open cockpit fuselage and a D-12 engine. A small loss in propulsive efficiency is indicated. Examples are given showing the application of the results to practical problems.
Date:
December 10, 1929
Creator:
Wood, Donald H.
System:
The UNT Digital Library
Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 1: Ordinary Ailerons on Rectangular Wings
"This report is the first in a series in which it is intended to compare the relative merits of all ordinary and some special forms of ailerons and other lateral control devices in regard to their effect on lateral controllability, lateral stability, and airplane performance. The comparisons are based on wind-tunnel test data, all the control devices being fitted to model wings having the same span, area, and airfoil section, and being subjected to the same series of force and rotation tests. The results are given for five different aileron movements: one with equal up-and-down deflection, one with average and one with extreme differential motion, one with upward deflection only, and one with the ailerons arranged to float with respect to the wing" (p. 357).
Date:
December 10, 1931
Creator:
Weick, Fred E. & Wenzinger, Carl J.
System:
The UNT Digital Library
Increasing the air charge and scavenging the clearance volume of a compression-ignition engine
The object of the investigation presented in this report was to determine the effects of increasing the air charge and scavenging the clearance volume of a 4-stroke-cycle compression-ignition engine having a vertical-disk form combustion chamber. Boosting the inlet-air pressure with normal valve timing increased the indicated engine power in proportion to the additional air inducted and resulted in smoother engine operation with less combustion shock. Scavenging the clearance volume by using a valve overlap of 145 degrees and an inlet-air boost pressure of approximately 2 1/2 inches of mercury produced a net increase in performance for clear exhaust operation of 33 percent over that obtained with normal valve timing and the same boost pressure. The improved combustion characteristics result in lower specific fuel consumption, and a clearer exhaust.
Date:
June 10, 1933
Creator:
Spanogle, J. A.; Hicks, C. W. & Foster, H. H.
System:
The UNT Digital Library
Strength Tests of Thin-Walled Duralumin Cylinders in Compression
"This report is the second of a series presenting the results of strength tests of thin-walled duralumin cylinders and truncated cones of circular and elliptic section. It contains the results obtained from compression tests on 45 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. In addition to the tests on duralumin cylinders, there are included the results of numerous tests on rubber, celluloid, steel, and brass cylinders obtained from various sources" (p. 585).
Date:
June 10, 1933
Creator:
Lundquist, Eugene E.
System:
The UNT Digital Library
Wind-Tunnel Tests on Combinations of a Wing With Fixed Auxiliary Airfoils Having Various Chords and Profiles
This report presents the results of wind tunnel tests on various auxiliary airfoils having three different airfoil sections and several different chord lengths in combination with a Clark Y model wing in a sufficient number of relative positions to determine the optimum with regard to certain criterions of aerodynamic performance. The airfoil sections included a symmetrical profile, one of medium camber, and a highly cambered one. The chord sizes of the auxiliary airfoils ranged from 7.5 to 25 percent of the chord of the main wing, and the span was equal to that of the main wing.
Date:
June 10, 1933
Creator:
Weick, Fred E. & Sanders, Robert
System:
The UNT Digital Library
A Flight Investigation of the Effect of Mass Distribution and Control Setting on the Spinning of the XN2Y-1 Airplane
"The investigation of the effect of mass distribution on the spinning of airplanes initiated with tests on the NY-1 airplane has been continued by tests on another airplane in order to increase the scope of the information and to observe particularly the behavior of an airplane that shows considerable change in sideslip angle for its various conditions of spinning. The XN2Y-1 naval training biplane was used for the present tests in which changes of ballast along the longitudinal and lateral axes and changes of aileron, stabilizer, and elevator settings were made. The effects of these changes on the steady spin were measured in flight' (p. 185).
Date:
January 10, 1934
Creator:
Scudder, N. F.
System:
The UNT Digital Library
Analysis of 2-Spar Cantilever Wings With Special Reference to Torsion and Load Transference
"This paper deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined" (p. 45).
Date:
April 10, 1934
Creator:
Kuhn, Paul
System:
The UNT Digital Library
Vibration response of airplane structures
This report presents test results of experiments on the vibration-response characteristics of airplane structures on the ground and in flight. It also gives details regarding the construction and operation of vibration instruments developed by the National Advisory Committee for Aeronautics.
Date:
May 10, 1934
Creator:
Theodorsen, Theodore & Gelalles, A. G.
System:
The UNT Digital Library
General equations for the stress analysis of rings
In this report it is shown that the shear, axial force, and moment at one point in a simple ring subjected to any loading condition can be given by three independent equations involving certain integrals that must be evaluated regardless of the method of analysis used. It is also shown how symmetry of the ring alone or of the ring and the loading about 1 or 2 axes makes it possible to simplify the three equations and greatly reduces the number of integrals that must be evaluated. Application of the general equations presented in this report to practical problems in the stress analysis of rings makes it possible to shorten, simplify, and systematize the calculations for both simple and braced rings. Three illustrative problems are included to demonstrate the application of the general equations to a simple ring with different loadings.
Date:
August 10, 1934
Creator:
Lundquist, Eugene E. & Burke, Walter F.
System:
The UNT Digital Library
Experimental investigation of the Robinson-type cup anemometer
This report presents the results of wind tunnel tests on a Robinson-type anemometer. The investigation covered force measurements on individual cups, as well as static and dynamic torque measurements and calibrations on complete cup wheels. In the tests on individual cups 5 cup forms were used and in the measurements on complete cup wheels 4 cup wheels with 3 arm lengths for each cup wheel were tested. All the results are presented in graphical form.
Date:
October 10, 1934
Creator:
Brevoort, M. J. & Joyner, U. T.
System:
The UNT Digital Library
The Effect of Water Vapor on Flame Velocity in Equivalent Carbon Monoxide and Oxygen Mixtures
This report presents the results of an investigation to study the effect of water vapor upon the spatial speed of flame in equivalent mixtures of carbon monoxide and oxygen at various total pressures from 100 to 780 mm.hg. These results show that, within this pressure range, an increase in flame speed is produced by increasing the mole fraction of water vapor at least as far as saturation at 25 degrees c., and that the rate of this increase is greater the higher the pressure. It is evident that water vapor plays an important part in the explosive oxidation of carbon monoxide; the need for further experimental evidence as to the nature of its action is indicated.
Date:
January 10, 1935
Creator:
Fiock, Ernest F. & King, H. Kendall
System:
The UNT Digital Library
The Soap-Bubble Method of Studying the Combustion of Mixtures of Carbon Monoxide and Oxygen
This investigation is a detailed description of the soap-bubble, or constant-pressure, method as applied to the explosive oxidation of carbon monoxide. A series of values of the speed of flame in space in various mixtures of CO and O2 containing a constant percentage of water vapor was obtained by the constant-volume method. These results served as a guide in the perfection of the soap-bubble method.
Date:
January 10, 1935
Creator:
Fiock, Ernest F. & Roeder, Carl H.
System:
The UNT Digital Library
Investigation of Full-Scale Split Trailing-Edge Wing Flaps With Various Chords and Hinge Locations
This report gives the results of an investigation conducted in the NACA full-scale wind tunnel on a small parasol monoplane equipped with three different split trailing-edge wing flaps. The object of the investigation was to determine and correlate data on the characteristics of the airplane and flaps as affected by variation in flap chord, flap deflection, and flap location along the wing chord. The results give the lift, the drag, and the pitching moment characteristics of the airplane, and the flap forces and moments, the pressure distribution over the flaps and wing at one section, and the downwash characteristics of the flap and wing combinations.
Date:
May 10, 1935
Creator:
Wallace, Rudolf
System:
The UNT Digital Library
[Texas Cotton Industries Return of Capital Stock Tax: 1937]
Capital stock tax return of 1937 for Texas Cotton Industries. The return includes all necessary schedules.
Date:
February 10, 1937
Creator:
Texas Cotton Industries
System:
The Portal to Texas History
A study of the torque equilibrium of an autogiro rotor
From Summary: "Two improvements have been made in the method developed in NACA Reports nos. 487 and 591 for the estimation of the inflow velocity required to overcome a given decelerating torque in an autogiro rotor. At low tip-speed ratios, where the assumptions necessary for the analytical integrations of the earlier papers are valid, the expressions therein derived are greatly simplified by combining and eliminating terms with a view of minimizing the numerical computations required. At high tip-speed ratios, by means of charts based on graphical integrations, errors inherent in the assumptions associated with the analytical method are largely eliminated."
Date:
January 10, 1938
Creator:
Bailey, F. J., Jr.
System:
The UNT Digital Library
Dewitt County, Texas: Records of wells, driller's logs, water analyses, and map showing location of wells
Data complied regarding wells and other water resources, including water quality analysis, measurements, and other relevant information.
Date:
June 10, 1938
Creator:
United States. Work Projects Administration.
System:
The Portal to Texas History
The influence of directed air flow on combustion in spark-ignition engine
"The air movement within the cylinder of the NACA combustion apparatus was regulated by using shrouded inlet valves and by fairing the inlet passage. Rates of combustion were determined at different inlet-air velocities with the engine speed maintained constant and at different engine speeds with the inlet-air velocity maintained approximately constant. The rate of combustion increased when the engine speed was doubled without changing the inlet-air velocity; the observed increase was about the same as the increase in the rate of combustion obtained by doubling the inlet-air velocity without changing the engine speed" (p. 313).
Date:
October 10, 1938
Creator:
Rothrock, A. M. & Spencer, R. C.
System:
The UNT Digital Library
Dawson County, Texas: Records of wells, driller's logs, water analyses, and map showing location of wells
Data complied regarding wells and other water resources, including water quality analysis, measurements, and other relevant information.
Date:
December 10, 1938
Creator:
Cumley, J. C.
System:
The Portal to Texas History
Preliminary wind-tunnel investigation of an NACA 23012 airfoil with various arrangements of venetian-blind flaps
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of venetian-blind flaps to determine the aerodynamic section characteristics as affected by the over-all flap chord, the chords of the slats used to form the flap, the slat spacing, the number of slats and the position of the flap with respect to the wing. Complete section data are given in the form of graphs for all the combinations tested.
Date:
January 10, 1939
Creator:
Wenzinger, Carl J. & Harris, Thomas A.
System:
The UNT Digital Library
Wind-tunnel investigation of NACA 23012, 23021, and 23030 airfoils with various sizes of split flap
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-chord NACA and 23021, and 23030 airfoils with split flaps 10, 20, 30, and 40 percent of the wing chord to determine the section aerodynamic characteristics of the airfoils as affected by airfoil thickness, flap chord, and flap deflection. The complete section aerodynamic characteristics of all the combinations tested are given in the form of graphs of lift, drag, and pitching-moment coefficients, and certain applications to aerodynamic design are discussed.
Date:
March 10, 1939
Creator:
Wenzinger, Carl J. & Harris, Thomas A.
System:
The UNT Digital Library
Irion County, Texas: Records of wells and springs, drillers' logs, water analyses, and map showing locations of wells and springs
Data complied regarding wells and other water resources, including water quality analysis, measurements, and other relevant information.
Date:
June 10, 1941
Creator:
United States. Work Projects Administration.
System:
The Portal to Texas History