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Technical Report Archive and Image Library
148
Office of Scientific & Technical Information Technical Reports
108
National Advisory Committee for Aeronautics Collection
92
TRAIL Microcard Collection
31
Texas State Publications
4
Government Documents A to Z Digitization Project
1
Texas Attorney General Opinions
1
USDA Farmers' Bulletins
1
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NACA Research Memorandums
61
NACA Technical Notes
26
United States Geological Survey Reports
17
Trace elements investigations report
13
Atomic Energy Commission Reports
9
Hanford Works Reports
9
ORNL (Series)
5
Oak Ridge National Laboratory Reports
5
Los Alamos National Laboratory Reports
4
NACA Technical Reports
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Potato growing in the South.
Provides detailed information on potato farming in 13 different southern states including cultivation and soil conservation practices, and identifying and controlling diseases and insects.
Date:
April 1956
Creator:
Dykstra, Theodore P. (Theodore Peter), 1896-1979 & Reid, W. J. (William John), 1902-
Object Type:
Book
System:
The UNT Digital Library
Progress Report on AEC Contract on Research and Development Program on Scintillation Crystals: Period 1 January 1956 to 1 April 1956
From Abstract: "This report covers the preliminary literature survey and the screening of activated cesium iodide and several alkali halides to qualitatively determine their luminerscence. The report also includes a proposal of the future work and a proposed budget for the 1957 fiscal year."
Date:
April 25, 1956
Creator:
Beadle, Robert
Object Type:
Report
System:
The UNT Digital Library
Effect of Combustion Gas Properties on Turbojet-Engine Performance With Hydrogen as Fuel
Memorandum presenting an analysis comparing engine performance determined by use of a method involving adjustment of engine cycle calculations using JP-4 fuel with performance obtained using hydrogen as a fuel.
Date:
April 10, 1956
Creator:
English, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System
Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
Date:
April 9, 1956
Creator:
Scallion, William I.
Object Type:
Report
System:
The UNT Digital Library
Pressure Distributions at Mach Numbers of 1.6 and 1.9 of a Conically Cambered Wing of Triangular Plan Form With and Without Pylon-Mounted Engine Nacelles
Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. The pressure data obtained during this investigation indicate that the low-pressure region existing on the upper surface over the forward part of the wing was spread over a larger proportion of the local chord than would be the case for an uncambered wing.
Date:
April 20, 1956
Creator:
Phelps, E. Ray
Object Type:
Report
System:
The UNT Digital Library
Perforated Sheets as a Porous Material for Distributed Suction and Injection
Note presenting measurements made of the resistance to air flow of a series of perforated metal sheets with open areas ranging from less than 1 percent up to 41 percent. The results showed that the permeability of a perforated sheet is governed principally by its open-area ratio. The number of holes per square inch, the sheet thickness, and the shape of the individual holes had little or no effect on permeability.
Date:
April 1956
Creator:
Dannenberg, Robert E.; Gambucci, Bruno J. & Weiberg, James A.
Object Type:
Report
System:
The UNT Digital Library
The Interference Effects of a Body on the Spanwise Load Distributions of Two 45 Degree Sweptback Wings of Aspect Ratio 8.02 from Low-Speed Tests
From Summary: "Tests of two wing-body combinations have been conducted in the Langley 19-foot pressure tunnel at a Reynolds number of 4 x 10(exp 6) and a Mach number of 0.19 to determine the effects of the bodies on the wing span load distributions. The wings had 45 degrees sweepback of the quarter-chord line, aspect ratio 8.02, taper ratio 0.45, and incorporated 12-percent-thick airfoil sections streamwise. One wing was untwisted and uncambered whereas the second wing incorporated both twist and camber. Identical bodies of revolution, of 10:1 fineness ratio, having diameter-to-span ratios of 0.10, were mounted in mid-high-wing arrangements."
Date:
April 1956
Creator:
Martina, Albert P.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a 1/22-Scale of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Static Longitudinal Stability and Control and Performance Characteristics at Transonic Speeds
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.
Date:
April 26, 1956
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
Some Flight Data for the Chance Vought Regulus 2 Missile
Report discussing tests of a model of the Chance Vought Regulus II missile to determine the lift, static stability, dynamic stability, trim, duct information, and drag for a range of Mach numbers.
Date:
April 23, 1956
Creator:
Wineman, Andrew R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96
Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Date:
April 24, 1956
Creator:
Hadaway, William M.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of Air-turborocket Engine Performance Including Effects of Component Changes
Report presenting analytical estimates of the thrust, efficiency, drag, and weight of the air-turborocket engine. The effects of changes in the engine components on design and off-design performance are emphasized. Results regarding the performance, effect of design parameters, effect of subsonic cruising Mach number, geometry variations, engine weight estimates, and comparison with turbojet engines are provided.
Date:
April 6, 1956
Creator:
Luidens, Roger W. & Weber, Richard J.
Object Type:
Report
System:
The UNT Digital Library
An analysis of estimated and experimental transonic downwash characteristics as affected by plan form and thickness for wing and wing-fuselage configurations
From Introduction: "The purpose of the present paper is to present summary of the information gleaned from various transonic-bump investigations of wing and wing-fuselage configurations at two representative tail heights and to compare these results with theoretical estimations made in subsonic and supersonic Mach number range."
Date:
April 1956
Creator:
Weil, Joseph; Campbell, George S. & Diederich, Margaret S.
Object Type:
Report
System:
The UNT Digital Library
Vapor-Phase Oxidation and Spontaneous Ignition-Correlation and Effect of Variables
Note presenting the spontaneous ignition temperatures of eight structurally different hydrocarbons, which were correlated with the behavior of the same hydrocarbons toward vapor-phase oxidation. The results indicated that reducing the stoichiometry of a hydrocarbon-oxygen gas mixture to less than unity decreases the extent of oxidation, other conditions remaining unchanged.
Date:
April 1956
Creator:
Swarts, Donald E. & Orchin, Milton
Object Type:
Report
System:
The UNT Digital Library
Calculations of the rate of thermal dissociation of air behind normal shock waves at Mach numbers of 10, 12, and 14
Report presenting the rate equation for the dissociation of air, based on simple-collision theory, and the numerical values of the factors that enter it. The rate equation and conservation equations for a flowing dissociating gas are solved for the conditions behind normal shock waves at Mach numbers of 10, 12, and 14. Results regarding the adjustment of translation, rotation, and vibration and adjustment of dissociation are provided.
Date:
April 1956
Creator:
Wood, George P.
Object Type:
Report
System:
The UNT Digital Library
The Accuracy of the Substitute-Stringer Approach for Determining the Bending Frequencies of Multistringer Box Beams
"The accuracy of the substitute-stringer approach for including the effects of shear lag in the calculation of the transverse modes and frequencies of multistringer box beams is investigated. Box beams, the covers of which consist of normal-stress-carrying stringers on sheets which carry not only shear but also normal stress, are analyzed exactly. Frequencies of beams with various numbers of stringers, obtained by means of this exact analysis, serve to determine the possible accuracy of the frequencies obtained by the substitute-stringer approach" (p. 1).
Date:
April 1956
Creator:
Davenport, William W.
Object Type:
Report
System:
The UNT Digital Library
Flight investigation of the effectiveness of an automatic aileron trim control device for personal airplanes
Report presenting a flight investigation to determine the effectiveness of an automatic aileron trim control device installed in a persona airplane to augment the apparent spiral stability. The device utilizes a rate-gyro sensing element in order to switch an on-off type of control that operates the ailerons at a fixed rate through control centering springs. Results for the basic airplane, the airplane with automatic control, and the pilots' opinion of the automatic system are provided.
Date:
April 1956
Creator:
Phillips, William H.; Kuehnel, Helmut A. & Whitten, James B.
Object Type:
Report
System:
The UNT Digital Library
On Panel Flutter and Divergence of Infinitely Long Unstiffened and Ring-Stiffened Thin-Walled Circular Cylinders
Note presenting a theoretical investigation of the panel flutter and divergence of infinitely long, unstiffened and ring-stiffened thin-walled circular cylinders. Linearized unsteady potential-flow theory is utilized in conjunction with Donnell's cylinder theory to obtain equilibrium equations for panel flutter.
Date:
April 1956
Creator:
Leonard, Robert W. & Hedgepeth, John M.
Object Type:
Report
System:
The UNT Digital Library
Effect of shallow water on the hydrodynamic characteristics of a flat-bottom planing surface
Report presenting an investigation on the tank no. 2 monorail to determine the effect of shallow water on the hydrodynamic characteristics of a flat-bottom planing surface. Values of lift, drag, and trimming moment at a constant speed over a range of trim, wetted lengths, and clearances between the model and a false bottom in the tank.
Date:
April 1956
Creator:
Christopher, Kenneth W.
Object Type:
Report
System:
The UNT Digital Library
A Theory for the Elastic Deflections of Plates Integrally Stiffened on One Side
Note presenting an elastic-deflection theory for anisotropic plates which exhibit coupling between bending and stretching. The theory provides a basis for analyzing plates integrally stiffened on one side. Example calculations show that in the case of a simply supported square plate loaded in compression and with equal flexural stiffnesses in the principal directions, coupling may significantly lower the in-plane compressive load at which deflections grow rapidly.
Date:
April 1956
Creator:
Crawford, Robert F.
Object Type:
Report
System:
The UNT Digital Library
Some effects of fuselage flexibility on longitudinal stability and control
Report presenting some effects of fuselage flexibility on longitudinal stability and control of a large airplane as determined by application of a semirigid analytical technique. The consideration of fuselage flexibility appears to introduce no serious problems as far as dynamic longitudinal stability in the subcritical speed range is determined. Results regarding period and damping, longitudinal stability margins, and elevator-control motion are provided.
Date:
April 1956
Creator:
Klawans, Bernard B. & Johnson, Harold I.
Object Type:
Report
System:
The UNT Digital Library
Analysis of a spin and recovery from time histories of attitudes and velocities as determined for a dynamic model of a contemporary fighter airplane in the free-spinning tunnel
From Introduction: "In this paper are presented descriptions of the camera setups and associated equipment, the equations and methods used in determining the model attitudes and motions from the film, and time-history curves of the variables of the spin and recovery investigated. Discussions of the nature of the spin and recovery obtained and of factors ostensibly affecting these motions are included."
Date:
April 1956
Creator:
Scher, Stanley H.
Object Type:
Report
System:
The UNT Digital Library
Initial results of a flight investigation of a gust-alleviation system
Report presenting a flight investigation of a gust-alleviation system designed to alleviate normal accelerations in the frequency range of 0 to 2 cycles per second. The system is designed to improve passenger comfort in turbulent air. The system is capable of reducing the normal accelerations due to gusts by 50 percent at 0.6 cycle per second and 40 percent at a frequency of 2 cycles per second.
Date:
April 1956
Creator:
Kraft, Christopher C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Intensity, scale, and spectra of turbulence in mixing region of free subsonic jet
Report presents the results of the measurements of intensity of turbulence, the longitudinal and lateral correlation coefficients, and the spectra of turbulence in a 3.5-inch-diameter free jet measured with hot-wire anemometers at exit Mach numbers from 0.2 to 0.7 and Reynolds numbers from 192,000 to 725,000.
Date:
April 24, 1956
Creator:
Laurence, James C.
Object Type:
Report
System:
The UNT Digital Library
Three-dimensional transonic flow theory applied to slender wings and bodies
The present paper re-examines the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, giving special attention to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow, that is, flow at free-stream Mach number 1.
Date:
April 2, 1956
Creator:
Heaslet, Max A. & Spreiter, John R.
Object Type:
Report
System:
The UNT Digital Library