Resource Type
Serial/Series Title
NACA Research Memorandums
424
Atomic Energy Commission Reports
387
NACA Technical Notes
375
GJBX
197
United States Department of Energy Grand Junction Office Reports
169
United States Geological Survey Reports
132
NACA Technical Memorandums
121
NACA Wartime Reports
106
Argonne National Laboratory Reports
97
AEC research and development report
80
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2,276 Matching Results
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Icing Frequencies Experienced During Climb and Descent by Fighter-Interceptor Aircraft
"Data and analyses are presented on the relative frequencies of occurrence and severity of icing cloud layers encountered by jet aircraft in the climb and descent phases of flights to high altitudes. Fighter-interceptor aircraft operated by the Air Defense Command (USAF) at bases in the Duluth and Seattle areas collected the data with icing meters installed for a 1-year period. The project was part of an extensive program conducted by the NACA to collect Icing cloud data for evaluating the icing problem relevant to routine operations" (p. 1).
Date:
July 1958
Creator:
Perkins, Porter J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content
"Flight icing-rate data obtained in a dense and abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer" (p. 1).
Date:
July 11, 1951
Creator:
Perkins, Porter J. & Kline, Dwight B.
Object Type:
Report
System:
The UNT Digital Library
Photomicrographic Investigation of Spontaneous Freezing Temperatures of Supercooled Water Droplets
"A photomicrographic technique for investigating seupercooled water droplets has been devised and. used. to determine the spontaneous freezing temperatures of seupercooled water droplets of the size ordinarily found. in the atmosphere. The freezing temperatures of 4527 droplets ranging from 8.75 to 1000 microns in diameter supported on a platinum surface and 571 droplets supported on copper were obtained. The average spontaneous freezing temperature decreased with decrease in the size of the droplets" (p. 1).
Date:
July 1950
Creator:
Dorsch, Robert G. & Hacker, Paul T.
Object Type:
Report
System:
The UNT Digital Library
Abacus for the Reduction of English Measures to the Metric System and Vice Versa
This report presents a description of an abacus with three scales: one for English measures, one for metric measures, and one with the "points of reduction", as well as construction details. There is also a detailed description on how to use the abacus.
Date:
July 1921
Creator:
Tenani, Mario
Object Type:
Report
System:
The UNT Digital Library
Study of Chromium-Frit-Type Coatings for High-Temperature Protection of Molybdenum
"The achievement of more compact and efficient power plants for aircraft is dependent, among other factors, on the perfection of heat-resisting materials that are superior to those in current use. Molybdenum is one of the high-melting metals (melting point, 4750 F). It is fairly abundant and also can be worked into many of the shapes required in modern power plants. To permit its widespread use at elevated temperatures, however, some means must first be found to prevent its rapid oxidation" (p. 1).
Date:
July 1951
Creator:
Moore, D. G.; Bolz, L. H.; Pitts, J. W. & Harrison, W. N.
Object Type:
Report
System:
The UNT Digital Library
Flexible Petrol Pipe
Report presenting an examination of flexible piping and some of the difficulties involved in creating satisfactory flexible pipe. The joint used to assist in the flexibility of the pipe is illustrated and described.
Date:
July 1921
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Impingement of Water Droplets on NACA 65A004 Airfoil at 8 Degree Angle of Attack
The trajectories of droplets in the air flowing past an NACA 65AO04 airfoil at an angle of attack of 8 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the same airfoil at an angle of attack of 4 deg.
Date:
July 1954
Creator:
Brun, Rinaldo J.; Gallagher, Helen M. & Vogt, Dorothea E.
Object Type:
Report
System:
The UNT Digital Library
The Problem of Fuel for Aviation Engines
Note presenting the physical properties which may be demanded of fuels for aviation use and the means that may be adopted by the engine manufacturers to properly meet the demands necessitated by the use of the fuel. Some of the factors that must be considered include its composition, the quantity available, the price per heat unit, and the possibility of keeping stocks in aerial ports both at home and abroad.
Date:
July 1921
Creator:
Kutzbach & James, W. S.
Object Type:
Report
System:
The UNT Digital Library
The Caproni Seaplane
The Caproni Company recently built a seaplane of unusual design. The main supporting surfaces consisted of three triplanes in tandem, the lower wings being attached to the hull, which was described as providing accommodation for a hundred passengers. On one of the first flights, the seaplane fell into a lake, nose down, and was destroyed. The authors wish to show that this failure could have been predicted.
Date:
July 1921
Creator:
Munk, Max
Object Type:
Report
System:
The UNT Digital Library
The Dynamometer Hub for the Testing Propellers and Engines During Flight
The need for a device to measure flight resistance, engine and propeller power, and efficiency during flight grew in proportion to the demand for increased flying capacity in military types of aircraft. Here, a dynamometer hub was inserted between the engine and the propeller. Taken as a whole, the tests that were conducted show that though the dynamometer is a sensitive instrument liable to numerous derangements, it is undeniably useful even in its present form, when handled with care and skill.
Date:
July 1921
Creator:
Enoch, O.
Object Type:
Report
System:
The UNT Digital Library
Static Testing and Proposed Standard Specifications
Static tests fall into two groups, the first of which is designed to load all members of the structure approximately in accordance with the worst loads which they carry in flight, while the second is directed to the testing of specific members which are suspected of weakness and which are difficult to analyze mathematically. The nature of the loading in the second type is different for every different test, but the purpose of the first is defined clearly enough to permit the adoption of some standard set of loading specifications, at least for airplanes of normal design. Here, an attempt is made to carry through an analysis leading to such a standard, the goal being the determination of a load which will simultaneously impose on every member of the airplane structure a stress equal to the worst it will carry in flight.
Date:
July 1920
Creator:
Warner, E. P.
Object Type:
Report
System:
The UNT Digital Library
Notes on the Design of Supercharged and Over-dimensioned Aircraft Engines
The author discusses the limited benefits of supercharging motors and some of the factors that make supercharging less beneficial than it initially appears.
Date:
July 1920
Creator:
Schwager, [Otto]
Object Type:
Report
System:
The UNT Digital Library
Duralumin
Various properties of duralumin as used in aircraft construction are discussed, including the effects of temperature, working, tempering, and strength.
Date:
July 1920
Creator:
Unger, E. & Schmidt, E.
Object Type:
Report
System:
The UNT Digital Library
Theory of Lifting Surfaces
The general basis of the theory of lifting surfaces is discussed. The problem of the flow of a fluid about a lifting surface of infinite span is examined in terms of the existence of vortexes in the current. A general theory of permanent flow is discussed. Formulas for determining the influence of aspect ratio that may be applied to all wings, whatever their plane form, are given.
Date:
July 1920
Creator:
Prandtl, L.
Object Type:
Report
System:
The UNT Digital Library
Evaluation of Some Aerodynamic Controls for a Low Aspect Ratio Missile
"Results of a static stability controls investigation carried out with a very low-aspect-ratio delta-winged missile are presented. Control effectiveness comparisons are made for tail, canard, and nose control configurations with respect to angle of attack, angle of bank, and Mach number. Trim capabilities of the various configurations are also presented" (p. 1).
Date:
July 17, 1958
Creator:
Winovich, Warren & Higdon, Nancy S.
Object Type:
Report
System:
The UNT Digital Library
Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines
Memorandum presenting performance calculations for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date:
July 22, 1958
Creator:
Dugan, James F., Jr.
Object Type:
Report
System:
The UNT Digital Library
Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct
Report described five short multielement turbojet combustors for use with hydrogen fuel and their performance. Information about the combustion efficiency, temperature profiles, pressure loss, durability, and comparison with previous short combustors is included.
Date:
July 22, 1958
Creator:
Jones, Robert E. & Rayle, Warren D.
Object Type:
Report
System:
The UNT Digital Library
Experimental and Theoretical Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil
Note presenting a low-turbulence wind tunnel investigation of an NACA 64A010 airfoil with a porous surface of sintered bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by use of suction to produce continuous inflow through the surface of the model. Results regarding the uncompartmented model, compartmented model, observations on stability of laminar boundary layer, and theoretical calculations are provided.
Date:
July 1949
Creator:
Burrows, Dale L.; Braslow, Albert L. & Terervin, Neal
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages
Report presenting an investigation to experimentally determine the effectiveness of air cooling several turbine-blade configurations in a turbojet engine. The results obtained with the first configuration, which was a hollow blade shell with 10 tube inserts, are presented. A description of factors leading to the design are provided as well as the correlated cooled-blade temperatures, solid-blade temperatures, cooling-air-temperature increase through radial passages, and blade failure are provided.
Date:
July 30, 1950
Creator:
Ellerbrock, Herman H., Jr. & Stepka, Francis S.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing
Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.
Date:
July 8, 1953
Creator:
Phelps, E. Ray
Object Type:
Report
System:
The UNT Digital Library
Comparative Study of Turbofan and Turbojet Engines
Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
Date:
July 19, 1957
Creator:
Kaufman, Harold R.; Benser, William A. & Gabriel, David S.
Object Type:
Report
System:
The UNT Digital Library
Transonic Flutter Characteristics of a Cambered A-Plan-Form Wing With and Without Simulated Nacelles
Report presenting an experimental investigation to determine the effects of simulated engine nacelles on the flutter characteristics of a cambered A-plan-form wing with 45 degree sweepback of the leading edge, an aspect ratio of 3.6, and a taper ratio of 0.14. Results regarding a wing-mount fixed and a model with wing mount free are provided.
Date:
July 10, 1957
Creator:
Kelly, H. Neale
Object Type:
Report
System:
The UNT Digital Library
Handbook of Structural Stability Part 2: Buckling of Composite Elements
"The local buckling of stiffener sections and the buckling of plates with sturdy stiffeners are reviewed, and the results are summarized in charts and tables. Numerical values of buckling coefficients are presented for longitudinally compressed stiffener sections of various shapes, for stiffened plates located in longitudinal compression and in shear, and for stiffened cylinders loaded in torsion. Although the data presented consist primarily of elastic-buckling coefficients, the effects of plasticity are discussed for a few special cases" (p. 1).
Date:
July 1957
Creator:
Becker, Herbert
Object Type:
Report
System:
The UNT Digital Library
A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge
From Summary: "Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possibility of drag reduction for a particular case."
Date:
July 1958
Creator:
Pitts, William C. & Nielsen, Jack Norman
Object Type:
Report
System:
The UNT Digital Library