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Investigation of heat transfer from a stationary and rotating ellipsoidal forebody of fineness ratio 3
From Summary: "The convective heat transfer from the surface of an ellipsoidal forebody of fineness ratio 3 and 20-inch maximum diameter was investigated in clear air for both stationary and rotating operation over a range of conditions including air speeds up to 240 knots, rotational speeds up to 1200 rpm, and angles of attack of 0 deg, 3 deg, and 6 deg. The results are presented in the form of heat-transfer coefficients and the correlation of Nusselt and Reynolds numbers. Both a uniform surface temperature and a uniform input heater density distribution were used."
Date:
November 1956
Creator:
Lewis, James P. & Ruggeri, Robert S.
System:
The UNT Digital Library
Impingement of Water Droplets on NACA 65A004 Airfoil and Effect of Change in Airfoil Thickness from 12 to 4 Percent at 4 deg Angle of Attack
From Summary: "The trajectories of droplets in the air flowing past an NACA 65A004 airfoil at an angle of attack of 4 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. The effect of a change in airfoil thickness from 12 to 4 percent at 4 deg angle of attack is presented by comparing the impingement calculations for the NACA 65A004 airfoil with those for the NACA 65(sub 1)-208 and 65(sub 1)-212 airfoils."
Date:
November 1953
Creator:
Brun, Rinaldo J.; Gallagher, Helen M. & Vogt, Dorothea E.
System:
The UNT Digital Library
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section
From Introduction: "The present paper employs an approach believed to be novel in slender-body theory and is concerned with developing formulas for the forces and moments as well as the stability derivatives for general slender wing-body combinations."
Date:
November 1954
Creator:
Sacks, Alvin H.
System:
The UNT Digital Library
A Summary of Meteorological Conditions Associated With Aircraft Icing and a Proposed Method of Selecting Design Criterions for Ice-Protection Equipment
Note presenting data from various sources on the observed values of meteorological variables, liquid-water content, mean-effective droplet size, and temperature, which are pertinent to aircraft icing. A method is proposed for the selection of design criterions for ice-protection equipment. The data are divided into two broad cloud types, stratiform and cumuliform clouds, because the icing conditions are very different for the two types.
Date:
November 1951
Creator:
Hacker, Paul T. & Dorsch, Robert G.
System:
The UNT Digital Library
Impingement of Water Droplets on a Sphere
Droplet trajectories about a sphere in ideal fluid flow were calculated. From the calculated droplet trajectories the droplet impingement characteristics of the sphere were determined. Impingement data and equations for determining the collection efficiency, the area, and the distribution of impingement are presented in terms of dimensionless parameters. The range of flight and atmospheric conditions covered in the calculations was extended considerably beyond the range covered by previously reported calculations for the sphere.
Date:
November 1955
Creator:
Dorsch, Robert G.; Saper, Paul G. & Kadow, Charles F.
System:
The UNT Digital Library
Impingement of water droplets on NACA 65A004 airfoil at 0 degrees angle of attack
From Summary: "The trajectories of water droplets in the air flowing past an NACA 6511004 airfoil at a n angle of attack of 0 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 t o cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the same airfoil at angles of attack of 4 deg and 8 deg."
Date:
November 1955
Creator:
Brun, Rinaldo J. & Vogt, Dorothea E.
System:
The UNT Digital Library
The Photographic Recording of Small Motions
Methods and equipment for recording small and sometimes rapid motions by photographic means are described, and the efficacy of photographic recording in such instances is evaluated. The optical system consisting of the light source, the mirror or prism for transmitting motion to the emergent beam, and a means of bringing the rays into focus on the film are discussed. Attention is given to the critical issue of mirror mounting.
Date:
November 1920
Creator:
Norton, F. H.
System:
The UNT Digital Library
Italian and French Experiments on Wind Tunnels
Given here are the results of experiments conducted by Colonel Costanzi of the Italian Army to determine the influence of the surrounding building in which a wind tunnel was installed on the efficiency of the installation, and how the efficiency of the installation was affected by the design of the tunnel. Also given are the results of a series of experiments by Eiffel on 34 models of tunnels of different dimensions. This series of experiments was started in order to find out if, by changing the shape of the nozzle or of the diffuser of the large tunnel at Auteuil, the efficiency of the installation could be improved.
Date:
November 1920
Creator:
Knight, William
System:
The UNT Digital Library
An Investigation on the Effect of Raked Wing Tips
This investigation was carried out by request of the United States Air Service in the wind tunnel of the Massachusetts Institute of Technology. The results are here published by the National Advisory Committee for Aeronautics as it is thought that they may be of general interest. Wings of the R.A.F. 6 section are tested with various angles of rake, and it is found that although rake has very little effect, a positive or negative rake of 30 degrees is the best.
Date:
November 1921
Creator:
Norton, F. H.
System:
The UNT Digital Library
Göttingen Wind Tunnel for Testing Aircraft Models
Given here is a brief description of the Göttingen wind tunnel for the testing of aircraft models, preceded by a history of its development. Included are a number of diagrams illustrating, among other things, a sectional elevation of the wind tunnel, the pressure regulator, the entrance cone and method of supporting a model for simple drag tests, a three-component balance, and a propeller testing device, all of which are discussed in the text.
Date:
November 1920
Creator:
Prandtl, L.
System:
The UNT Digital Library
Horizontal Buoyancy in Wind Tunnels
Note presenting an examination of horizontal buoyancy in wind tunnels, including an examination of the relative flow, static pressure gradient, horizontal buoyancy computation, and methods of computation in practical use are provided.
Date:
November 1920
Creator:
Zahm, A. F.
System:
The UNT Digital Library
Experiments With Slotted Wings
Note presenting an investigation of various aspects of slotted wings, including some theoretical and experimental results and characteristics of certain slotted wings currently in production.
Date:
November 1921
Creator:
Lachmann, G.
System:
The UNT Digital Library
The Choice of Wing Sections for Airplanes
"The subject of the choice of an airfoil section is by no means a closed one, and despite the impossibility of making a single rule serve, it is quite practicable to deduce in a strictly rational manner a series of rules and formulas which are capable of being of the greatest use if we but confine ourselves to the consideration of one element of performance at a time. There are seven such elements of performance which are here taken up in turn. The seven are of different relative importance in different types of airplanes. The seven elements are: maximum speed regardless of minimum; maximum speed for given minimum; maximum speed range ratio; maximum rate of climb; maximum absolute ceiling; maximum distance non-stop; and maximum duration non-stop" (p. 1-2).
Date:
November 1921
Creator:
Warner, Edward P.
System:
The UNT Digital Library
Determination of Climbing Ability
"The vertical distribution of the pressure, temperature, and density of the atmosphere varies from day to day. Thus, rates of climb on different days cannot be compared directly, but must be corrected with reference to a standard rate of diminution of air density with increasing altitude. The following problem, therefore, has to be solved" (p. 1).
Date:
November 1923
Creator:
Blasius, H.
System:
The UNT Digital Library
Wind Tunnel Tests of Five Strut Sections in Yaw
In the first series of wind tunnel tests, the drag and cross wing force of all the struts were measured at a wind speed of 30 mph and at angles of yaw from 0 degrees to 20 degrees. To determine the magnitude of the VL effect, each strut was tested at zero yaw and at a series of speeds ranging from 15 to 38 mph. Although designed as fairings for cables, part of these sections gave such high crosswind forces that they seemed to have possibilities as airfoils.
Date:
November 1923
Creator:
Warner, Edward P.
System:
The UNT Digital Library
Air Resistance Measurements on Actual Airplane Parts
"For the calculation of the parasite resistance of an airplane, a knowledge of the resistance of the individual structural and accessory parts is necessary. The most reliable basis for this is given by tests with actual airplane parts at airspeeds which occur in practice. The data given here relate to the landing gear of a Siemanms-Schuckert DI airplane; the landing gear of a 'Luftfahrzeug-Gesellschaft' airplane (type Roland Dlla); landing gear of a 'Flugzeugbau Friedrichshafen' G airplane; a machine gun, and the exhaust manifold of a 269 HP engine" (p. 1).
Date:
November 1923
Creator:
Weiselsberger, C.
System:
The UNT Digital Library
The Elimination of Dead Center in the Controls of Airplanes With Thick Sections
"In several instances where control flaps are placed in the trailing edges of thick sections, it has appeared that a dead center (slackness or lack of control) exists about the neutral position. The condition was also experienced in the rudder action of the XB1A observation airplane. Examination of smoke pictures of the airflow around struts and airfoils indicates what may be the cause of the phenomenon" (p. 1).
Date:
November 1922
Creator:
Carroll, Thomas
System:
The UNT Digital Library
A Preliminary Study of Airplane Performance
Flight tests were carried out at the Langley Field laboratory of the NACA, on several airplanes for the purpose of determining their relative performance with the same engine and the same propeller. The method used consisted in flying each airplane on a level course and measuring the airspeed for the whole range of engine revolutions. In general the results show that a small change in the wing section or the wing area has but a slight effect upon the performance, but changes in those parts which cause the structural resistance have a very important effect.
Date:
November 1922
Creator:
Norton, F. H. & Brown, W. G.
System:
The UNT Digital Library
Tests on Riveted Joints in Sheet Duralumin
In making tension tests, the slippage of the joints was noted at three points across each joint. In addition, stress strain curves were obtained for plain tension specimens, and a chemical analysis was made of the sheet.
Date:
November 1923
Creator:
Rettew, H. F. & Thumin, G.
System:
The UNT Digital Library
Structural Weight of Aircraft as Affected by the System of Design
Various details of design or arrangement of the parts of airplane structures are shown and discussed, the use of these devices having resulted in the production of structures of adequate strength, yet of a weight less than one-half of the usual construction.
Date:
November 1924
Creator:
Hall, Charles Ward
System:
The UNT Digital Library
The Simplifying Assumptions, Reducing the Strict Application of Classical Hydrodynamics to Practical Aeronautical Computations
Note presenting a general method followed to simplify the numerical work in hydrodynamics, which consists of neglecting quantities of a lower order of magnitude. Four of the solutions covered in this report include the theory of the lateral air forces on airship hulls, theory of wing sections in a two-dimensional flow, theory of wings with a finite span, and propeller theory.
Date:
November 1924
Creator:
Munk, Max M.
System:
The UNT Digital Library
The Distribution of Loads Between the Wings of a Biplane Having Decalage
"It is known that in a biplane the load is not distributed equally between the wings. The presence of one wing will affect the lift characteristics of the other wings. A designer must know the total load that each wing carries in order that he may design an adequate structure. The purpose here is to determine the distribution of loads between the wings of a biplane at various angles of decalage, when the gap/chord ratio is one, and there is no stagger" (p. 1).
Date:
November 1927
Creator:
Mock, Richard M.
System:
The UNT Digital Library
An Altitude Chamber for the Study and Calibration of Aeronautical Instruments
"The design and construction of an altitude chamber, in which both pressure and temperature can be varied independently, was carried out by the NACA at the Langley Memorial Aeronautical Laboratory for the purpose of studying the effects of temperature and pressure on aeronautical research instruments. Temperatures from +20c to -50c are obtained by the expansion of CO2from standard containers. The chamber can be used for the calibration of research instruments under altitude conditions simulating those up to 45,000 feet" (p. 1).
Date:
November 1925
Creator:
Reid, H. J. E. & Kirchner, Otto E.
System:
The UNT Digital Library
A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing Conditions
Report presenting an equation for calculating the heat flow required from the surface of an internally heated windshield in order to prevent ice accretions during flight in specified icing conditions. Results regarding the internally heated windshield characteristics, external discharge windshields, and prediction of heating requirements for both types of windshields are provided.
Date:
November 1947
Creator:
Jones, Alun R.; Holdaway, George H. & Steinmetz, Charles P.
System:
The UNT Digital Library