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13,786 Matching Results
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Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers
Report presenting a paper in two parts about transition and turbulent boundary layers. The first part reviews the current problem of the instability of laminar boundary layers. The second part reviews the current state of knowledge of the mechanics of turbulent boundary layers and of the methods now being used for fundamental studies of the turbulent fluctuations in turbulent boundary layers.
Date:
April 1947
Creator:
Dryden, Hugh L.
Object Type:
Report
System:
The UNT Digital Library
Considerations of the Total Drag of Supersonic Airfoil Sections
The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under different conditions, the circular-arc airfoil may have a higher drag.
Date:
July 1947
Creator:
Ivey, H. Reese & Klunker, E. Bernard
Object Type:
Report
System:
The UNT Digital Library
Performance of B. M. W. 185-horsepower airplane engine
Report discusses the results of testing on a B.M.W. engine in an altitude chamber where temperature and pressure can be controlled to simulate flight at various altitudes. Results for various engine speeds, altitudes, and propeller speeds are provided.
Date:
April 13, 1922
Creator:
Sparrow, Stanwood Willston
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date:
July 1934
Creator:
Hubbard, John D. & Brescoll, George P.
Object Type:
Report
System:
The UNT Digital Library
Bending Tests of Metal Monocoque Fuselage Construction
Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Date:
November 1930
Creator:
Mossman, Ralph W. & Robinson, Russell G.
Object Type:
Report
System:
The UNT Digital Library
Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid
The methods of NACA TN No. 995 have been slightly modified and extended in include flows with circulation by considering the alteration of the singularities of the incompressible solution due to the presence of the hypergeometric functions in the analytic continuation of the solution. It was found that for finite Mach numbers the only case in which the nature of the singularity can remain unchanged is for a ratio of specific heats equal to -1. From a study of two particular flows it seems that the effect of geometry cannot be neglected, and the conventional "pressure-correction" formulas are not valid, even in the subsonic region if the body is thick, especially if there is a supersonic region in the flow.
Date:
June 1948
Creator:
Kuo, Yung-Huai
Object Type:
Report
System:
The UNT Digital Library
Tables and charts of flow parameters across oblique shocks
Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy.
Date:
August 1948
Creator:
Neice, Mary M.
Object Type:
Report
System:
The UNT Digital Library
A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow
Comparison of free-molecule-flow theory with the results of wind-tunnel tests performed to determine the drag and temperature-rise characteristics of a transverse circular cylinder.
Date:
1951
Creator:
Stalder, Jackson R.; Goodwin, Glen & Creager, Marcus O.
Object Type:
Report
System:
The UNT Digital Library
Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method
Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existing methods. These results indicate that the variational method will yield good approximate solution for flow past both thick and thin bodies at both high and low Mach numbers.
Date:
March 1951
Creator:
Wang, Chi-Teh
Object Type:
Report
System:
The UNT Digital Library
Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section
Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges.
Date:
June 1954
Creator:
Grant, Frederick C. & Cooper, Morton
Object Type:
Report
System:
The UNT Digital Library
Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique
Carpet plots included permit the selection of the blade camber and the design angle of attack required to fulfill a design vector diagram. Other carpet plots provide means for the prediction of off-design turning angles.
Date:
February 1957
Creator:
Felix, A. Richard
Object Type:
Report
System:
The UNT Digital Library
Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades
Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Date:
March 9, 1951
Creator:
Hubbartt, James E. & Schum, Eugene F.
Object Type:
Report
System:
The UNT Digital Library
Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Oxygen-Nitrogen System at Temperatures From 2000° to 5000° Degrees K
Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.
Date:
July 1948
Creator:
Huff, Vearl N. & Calvert, Clyde S.
Object Type:
Report
System:
The UNT Digital Library
The Vickers "Vendace": A Land or Sea Training Biplane
Circular describing the Vickers "Vendace", which is a land or sea training tractor biplane. Details of the design, wings, construction, control surfaces, fuselage, fabric, cockpits, fuel supply, landing gear, characteristics, and drawings are provided.
Date:
May 1926
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Potez 37R2 Military Airplane: A Two-Place Long-Distance Observation Monoplane
Circular presenting a description of the Potez 37R2 military airplane, which is a two-place long-distance observation monoplane. Details of the design, construction, components, characteristics, drawings, and photographs are provided.
Date:
September 1931
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
"Avimeta" Three-Engine Commercial Monoplane: Type A.V.M. 132
This is an all metal aircraft, including the wing coverings. Both the framework and the sheet-metal coverings are Alferium, made by Schneider Co. A description of the wing, fuselage, landing gear, engines, fuel tanks, characteristics, drawings, and photographs are provided.
Date:
December 1927
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Analysis of Wind-Tunnel Stability and Control Tests in Terms of Flying Qualities in Full-Scale Airplanes
From Summary: "The analysis of results of wind-tunnel stability and control tests of powered airplane models in terms of the flying qualities of full-scale airplanes is advocated. In order to indicate the topics upon which comments are considered desirable in the report of a wind-tunnel stability and control investigation and to demonstrate the nature of the suggested analysis, the present NACA flying-qualities requirements are discussed in relation to wind-tunnel tests. General procedures for the estimation of flying qualities from wind-tunnel tests are outlined."
Date:
October 1943
Creator:
Kayten, Gerald G.
Object Type:
Report
System:
The UNT Digital Library
Combat and bombing airplane, Amiot 120 B 3
The Amiot 120 B 3 is designed as a French combat aircraft. It can accept a variety of engines, and is equipped with 2 machine guns as well as specialized bomb sights and other combat equipment.
Date:
January 1927
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
The Measurement of Fuel-Air Ratio by Analysis for the Oxidized Exhaust Gas
"An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene" (p. 1).
Date:
1943
Creator:
Gerrish, Harold C. & Meem, J. Lawrence, Jr.
Object Type:
Report
System:
The UNT Digital Library
The Bernard 120 Seaplane (French): A 1400 hp Single-Seat Monoplane Racer
Circular presenting a description of the Bernard 120, which is a seaplane. Descriptions of the structural elements, engine, and fuel distribution system are provided.
Date:
March 1931
Creator:
Léglise, Pierre
Object Type:
Report
System:
The UNT Digital Library
The Lioré-Olivier "Le 0.240" Commercial Seaplane (French): A High-Wing Cantilever Monoplane
Circular presenting a description of the Le 0.240, which is a cantilever monoplane invented by the Lioré-Olivier Company. Information regarding the wings, profile, fuel tanks, construction, ailerons, hull, controls, and flight characteristics is provided.
Date:
February 1930
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
The Fiat "TR.1" Training and Touring Airplane (Italian): A Two-Place High-Wing Monoplane
Circular presenting a description of the Fiat T.R.1 airplane, which has been created for training and long-distance touring. Information regarding the fuel tanks, aircraft design, controls, tail characteristics, and flight characteristics is provided.
Date:
December 1930
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
The Dyle and Bacalan "DB 70" Commercial Airplane (French): An All-Metal High-Wing Monoplane
Report presenting a description of the Dyle and Balaclan DB 70, which is a commercial airplane with a very thick wing. Details of the fuselages, wings, passenger and pilot spaces, ability to function as an ambulance airplane, and flying qualities are provided.
Date:
March 1930
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
The Morane Sauliner 222 Airplane (French): A Single-Seat Pursuit Monoplane
Circular presenting the Morane Saulnier 222 airplane, which is a single-seat pursuit monoplane. A description of the components, design, characteristics, performance, photographs, and drawings are provided.
Date:
December 1929
Creator:
Frachet, André
Object Type:
Report
System:
The UNT Digital Library