Collection
Technical Report Archive and Image Library
431
National Advisory Committee for Aeronautics Collection
366
Texas Attorney General Opinions
258
Office of Scientific & Technical Information Technical Reports
93
TRAIL Microcard Collection
44
World War Two Collection
24
Government Documents A to Z Digitization Project
23
World War Two Newsmaps
18
Texas State Publications
15
USDA Farmers' Bulletins
4
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841 Matching Results
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Deformation Analysis of Wing Structures
Note presenting theories of bending and torsion as applied to the problem of calculating the deflections in aircraft shell structures, particularly of wings. Bending as well as torsional deflections are discussed for wings without or with cut-outs.
Date:
July 1947
Creator:
Kuhn, Paul
Object Type:
Report
System:
The UNT Digital Library
Description of Stress-Strain Curves by Three Parameters
"A simple formula is suggested for describing the stress-strain curve in terms of three parameters; namely, Young's modulus and two secant yield strengths. Dimensionless charts are derived from this formula for determining the stress-strain curve, the tangent modulus, and the reduced modulus of a material for which these three parameters are given. Comparison with the tensile and compressive data on aluminum-alloy, stainless-steel, and carbon-steel sheet in NACA Technical Note No. 840 indicates that the formula is adequate for most of these materials" (p. 1).
Date:
July 1943
Creator:
Ramberg, Walter & Osgood, William R.
Object Type:
Report
System:
The UNT Digital Library
Design charts for cross-flow tubular intercoolers charge-through-tube type
Report presenting equations relating the various dimensions, air weight flow, and performance of a cross-flow tubular intercooler in which the charge flows through and the cooling air across the tubes. A method of determining and presenting the performance of a given intercooler at various operating conditions is indicated. Results regarding the cooling effectiveness equation, effect of primary intercooler variables, design charts, effect of tube arrangement on intercooler characteristics, and performance charts are provided.
Date:
July 1941
Creator:
Reuter, J. George & Valerino, Michael F.
Object Type:
Report
System:
The UNT Digital Library
The Design of Jet Pumps
This report shows that by applying both energy and impulse theorems the optimum throat dimension of the mixing nozzle and the best shape of intake can be predicted approximately in a relatively simple manner. The necessary length of the mixing nozzle follows from Prandtl's turbulent mixing theory. The calculations are carried out for the mixing of similar and dissimilar fluids.
Date:
July 1941
Creator:
Flügel, Gustav
Object Type:
Report
System:
The UNT Digital Library
Design, selection, and installation of aircraft heat exchangers
Report presenting a survey of aircraft heat exchangers in three parts: design, selection, and installation. Appendices give the physical properties of air, properties of standard atmosphere as defined by the Navy, Army, and NACA, and an impact-pressure chart.
Date:
July 1943
Creator:
Wood, George P. & Brevoort, Maurice J.
Object Type:
Report
System:
The UNT Digital Library
Determination of Barium in AAA Pitchblende Gangue
None
Date:
July 11, 1945
Creator:
McCoy, J. R. & Martin, G. L.
Object Type:
Report
System:
The UNT Digital Library
Determination of General Relations for the Behavior of Turbulent Boundary Layers
Report presenting an analysis of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. Results indicate that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter.
Date:
July 1943
Creator:
von Doenhoff, Albert E. & Tetervin, Neal
Object Type:
Report
System:
The UNT Digital Library
The Determination of Phosphorous in Rocks Containing Vanadium
From Abstract: "This paper describes a rapid routine procedure for the determination of phosphorous in the presence of vanadium. Vanadium is reduced with formic acid prior to precipitation of phosphorous as ammonium phosphomolybdate and the ammonium phosphomolybdate is weighed as such."
Date:
July 1949
Creator:
Randolph, R. B. & Grimaldi, F. S.
Object Type:
Report
System:
The UNT Digital Library
THE DETERMINATION OF PRESSURE DROP FACTORS THROUGH TYPICAL FUEL ELEMENT CHANNELS FOR HIGH TEMPERATURE GAS-COOLED THERMAL PILES
The initial phase of the pressure drop testing program on proposed fuel element design shapes for the high-temperature, gas-cooled power reactor, has been completed with the compilation of pressure drop data for the flatplate riveted-assembly type of unit, the ribbed cylinder type, the single bent-plate type both with and without rivets, the 13 hexagon-6 pentagon type, and the 7-hole graphite type. This phase of the program was conducted for the purpose of determining the equivalent skin-friction pressure drop factor for composite fuel element crosssections, and for determining the joint loss factors for varying degrees of misalignment of the fuel units in the fuel channels of the pile. (auth)
Date:
July 1, 1948
Creator:
Segaser, C.L.
Object Type:
Report
System:
The UNT Digital Library
Determination of the Stability and Control Characteristics of Airplanes from Tests of Powered Models
Report presenting a technique of testing wind tunnel powered models developed as a result of experience gained in the investigation of the static longitudinal and lateral staiblity and control characteristics of several powered models in the 7- by 10-foot wind tunnel. A discussion of the conditions to be investigated, methods of presenting and interpreting the data, and a suggested operating technique are given.
Date:
July 1942
Creator:
Recant, Isidore G.
Object Type:
Report
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 and to develop a rational method for the design of high-critical-speed nose inlets to meet desired requirements."
Date:
July 1945
Creator:
Baals, Donald D.; Smith, Norman F. & Wright, John B.
Object Type:
Report
System:
The UNT Digital Library
A Device for Measuring Sonic Velocity and Compressor Mach Number
Note presenting a device that measures the velocity of sound in fluids at stagnation and is especially adaptable to turbine and compressor testing for which the composition of the working fluid may be in doubt. The Helmholtz resonator is used for measuring sonic velocity and compressor Mach number in these devices.
Date:
July 1948
Creator:
Huber, Paul W. & Kantrowitz, Arthur
Object Type:
Report
System:
The UNT Digital Library
Diagrams for Calculation of Airfoil Lattices
"The field for curved blades is represented by a vortex series with a vortex removed at the blade point. Further, an example of calculation of a curved blade from this series is given, whereby the necessary accuracy required of the different methods in practice is shown according to the case considered" (p. 1).
Date:
July 1942
Creator:
Betz, Albert
Object Type:
Report
System:
The UNT Digital Library
The Dibutyl Carbitol Extraction Procedure for the Separation of Tubanyl and Phosphate Ions
"This report is concerned with the effectiveness of this washback procedure in reducing the phosphate concentration and also with other methods by which the simultaneous extraction of phosphate along with tuballoy may be minimized."
Date:
July 12, 1945
Creator:
Lord, E. J.; Andrews, L. J. & Gates, J. W.
Object Type:
Report
System:
The UNT Digital Library
Distribution of wave drag and lift in the vicinity of wing tips at supersonic speeds
From Summary: "The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at supersonic speeds was extended to include the effect of the region between the wing boundary and the foremost Mach wave from the wing leading edge. The effect of this region on the surface velocity potential has been determined by an equivalent function, which is evaluated over a portion of the wing surface. In this manner, the effect of angles of attack and yaw as well as the asymmetry of top and bottom wing surfaces may be calculated."
Date:
July 1947
Creator:
Evvard, John C.
Object Type:
Report
System:
The UNT Digital Library
Domestic disturbances
"This manual presents the principles for the employment of troops during domestic disturbances and the essential substances of the more important laws relating to the employment of military forces in the aid of civil authorities with the applicable War Department policies"
Date:
July 30, 1945
Creator:
United States. War Department.
Object Type:
Book
System:
The UNT Digital Library
Downwash and Dynamic Pressure at the Horizontal Tail of a Six-Engine Pusher-Propelled Airplane
Report discussing an investigation of the vertical plane of the elevator hinge line of a powered model of a bomber to determine the values of downwash and the dynamic-pressure ratio. The equations for calculating these values and the testing procedures are described.
Date:
July 19, 1948
Creator:
Furlong, G. Chester
Object Type:
Report
System:
The UNT Digital Library
Drag Corrections in High-Speed Wind Tunnels
In the vicinity of a body in a wind tunnel the displacement effect of the wake, due to the finite dimensions of the stream, produces a pressure gradient which evokes a change of drag. In incompressible flow this change of drag is so small, in general, that one does not have to take it into account in wind-tunnel measurements; however, in compressible flow it beoomes considerably larger, so that a correction factor is necessary for measured values. Correction factors for a closed tunnel and an open jet with circular cross sections are calculated and compared with the drag - corrections already bown for high-speed tunnnels.
Date:
July 1947
Creator:
Ludwieg, H.
Object Type:
Report
System:
The UNT Digital Library
Drag Measurements of a Protruding 0.50-Caliber Machine Gun
Report presenting drag and cross-wind force measurements of a Browning 0.50-caliber M2 machine gun at a range of air speeds in the NACA wind tunnel. The gun protruded through the top of the tunnel wall into the air stream and tests were performed at a variety of angles in order to determine the power required to turn the gun against the aerodynamic forces and the horsepower absorbed in air drag by the protruding gun. Special attention is given to the jacket around the gun, which seems to provide the greatest amount of drag.
Date:
July 1941
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
Drag of Several Gunner's Enclosures at High Speeds
"The drag of several types of gunner's turrets, windshields, blisters, and other protuberances, including projecting guns, was investigated at speeds from 75 to 440 miles per hour in the NACA 8-foot high-speed wind tunnel. The various gunner's enclosures were represented by 1/10 and 1/7 full-size models on a midwing-fuselage combination representative of bomber types. Most of the usual types of retractable turrets are very poor aerodynamically; they caused wind drag increments, dependent upon the size of the turret relative to the fuselage and upon the speed, up to twice the drag of the fuselage alone" (p. 1).
Date:
July 1941
Creator:
Stack, John & Moberg, Richard J.
Object Type:
Report
System:
The UNT Digital Library
Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers
"With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method" (p. 1).
Date:
July 1947
Creator:
Regenscheit, B.
Object Type:
Report
System:
The UNT Digital Library
Dynamics of a turbojet engine considered as a quasi-static system
From Summary: "A determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and fixed area exhaust nozzle is presented. A generalized equation for transient behavior of the engine was developed; this equation was then verified by calculations using compressor and turbine performance charts extrapolated from equilibrium operating data and by experimental data obtained from an engine operated under transients in fuel flow."
Date:
July 27, 1949
Creator:
Otto, Edward W. & Taylor, Burt L., III
Object Type:
Report
System:
The UNT Digital Library
EARLY METHODS FOR CASTING URANIUM AT IOWA STATE COLLEGE
None
Date:
July 1, 1945
Creator:
Gray, C.F.
Object Type:
Report
System:
The UNT Digital Library
Economy of internally cooling only the overheated cylinders of aircraft engines
Report presenting an analysis of cylinder-to-cylinder temperature and mixture distributions of four different aircraft engines to determine the possible economy of automatically supply water or additional fuel to only those cylinders having excessive temperatures. The cooling problem as distinguished from the fuel-knock problem was studied and an analysis limited to those cases in which additional cooling is ordinarily obtained by carburetor enrichment was made.
Date:
July 1945
Creator:
Biermann, Arnold E.; Miller, George R. & Henneberry, Hugh M.
Object Type:
Report
System:
The UNT Digital Library