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Variation of Local Liquid-Water Concentration About and Ellipsoid of Fineness Ratio 5 Moving in a Droplet Field
From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 5 (which often approximates the shape of an aircraft fuselage or missile) were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid in flight through a droplet field varies considerably and under some conditions may be several times the free-stream concentration."
Date:
July 1954
Creator:
Dorsch, Robert G. & Brun, Rinaldo J.
System:
The UNT Digital Library
A Simplified Instrument for Recording and Indicating Frequency and Intensity of Icing Conditions Encountered in Flight
Memorandum presenting an instrument for recording and indicating the frequency and intensity of aircraft icing conditions to obtain statistical icing data over worldwide air routes during routine airline operations. Data of this type is needed to provide pertinent meteorological information necessary for the optimum design of ice-protection systems. The features that make this particular instrument desirable include the simplicity of operation, freedom from maintenance and operating problems, automatic operation upon encountering an icing condition, visual indications of icing intensity available to the pilot, total weight of 18 pounds, and continuous recorded data.
Date:
July 3, 1951
Creator:
Perkins, Porter J.; McCullough, Stuart & Lewis, Ralph D.
System:
The UNT Digital Library
A Probability Analysis of the Meteorological Factors Conducive to Aircraft Icing in the United States
Note presenting meteorological icing data obtianed in flight in the United States that is analyzed statistically and used to develop methods for the determination of the various simultaneous combinations of the three basic icing parameters and the probability of exceeding any specified group of values of liquid-water content associated simultaneously with temperature and drop-diameter values. A mathematical basis is also provided for the future statistical analysis of meteorological icing data that can be obtained throughout the world.
Date:
July 1952
Creator:
Lewis, William & Bergrun, Norman R.
System:
The UNT Digital Library
Preliminary Data on Rain Deflection from Aircraft Windshields by Means of High-Velocity Jet-Air Blast
From Summary: "A preliminary experimental investigation is being conducted to determine the feasibility of preventing rain from impinging on aircraft windshields by means of high-velocity jet-air blast. The results indicate that rain deflection by jet blast appears feasible for flight speeds comparable with landing and take-off speeds of interceptor-type jet aircraft; however, attainment of good visibility through the mist generated by raindrop breakup presents a problem. For the simulated windshield and the lower windshield angles used in the investigation, air-flow rates of the order of 3.3 pounds per minute of unheated air per inch of windshield span were required for adequate rain deflection at a free-stream velocity of 135 miles per hour."
Date:
July 25, 1955
Creator:
Ruggeri, Robert S.
System:
The UNT Digital Library
Hydrodynamic and Aerodynamic Tests of a Family of Models of Seaplane Floats With Varying Angles of Dead Rise: N.A.C.A. Models 57-A, 57-B, and 57-C
Report presenting testing of three models of V-bottom floats for twin-float seaplanes with varying angles of dead rise were tested in a tank and a wind tunnel. Results regarding the effect of angle of dead rise, height and amount of spray at hump speed, aerodynamic drag, effect of cross-sectional shape and load coefficients, and spray strips are provided.
Date:
July 1939
Creator:
Parkinson, John B.; Olson, Roland E. & House, Rufus O.
System:
The UNT Digital Library
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.
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.
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.
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
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.
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
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.
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.
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
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.
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.
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]
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.
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.
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.
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.
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.
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
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.
System:
The UNT Digital Library