Technical Report Archive and Image Library (TRAIL) - 117 Matching Results

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Atomization of Liquid Fuels Part 1: Relation Between Atomization and Combustion, Methods Employed for Determining the Size of Particles and Small Drops, Choice of Experimental Method

Description: In the present treatise we will consider chiefly the problem of solid injection in comparison with air injection. On leaving the valve or nozzle through one or more small openings, the fuel is split up into innumerable fine drops, which penetrate the combustion chamber in divergent directions in the form of a conical jet. The efficiency of this jet is judged from the following three viewpoints: 1) with respect to the fineness of atomization; 2) with respect to the direction or distribution of sprayed particles; 3) with respect to the penetration of the particles.
Date: September 1925
Creator: Kuehn
Partner: UNT Libraries Government Documents Department

Theory of Flapping Flight

Description: "Before attempting to construct a human-powered aircraft, the aviator will first try to post himself theoretically on the possible method of operating the flapping wings. This report will present a graphic and mathematical method, which renders it possible to determine the power required, so far as it can be done on the basis of the wing dimensions. We will first consider the form of the flight path through the air" (p. 1).
Date: October 1925
Creator: Lippisch, Alexander
Partner: UNT Libraries Government Documents Department

An Introduction to the Helicopter

Description: It is the object of this report to review briefly the aerodynamic and construction data already available regarding helicopters and to set forth the difficulties which must be met.
Date: 1925
Creator: Klemin, Alexander
Partner: UNT Libraries Government Documents Department

Results of Recent Experiments With Slotted Wings

Description: This report gives the results of a recent series of experiments performed on a wing designed for a cantilever monoplane. Both wings were trapezial in their ground plan, with their tips rounded elliptically. These wing sections combine all known devices for increasing the lift, namely, the slot, the increased camber and angle of attack by means of an aileron running the whole length of the span.
Date: January 1925
Creator: Lachmann, G.
Partner: UNT Libraries Government Documents Department

Experimental Determination of Pressure Drop Caused by Wire Gauze in an Air Stream

Description: "For several kinds of wire gauze the difference in static, dynamic and total or absolute pressure in front of and behind the gauze were determined for comparison with the pressure drop caused by an airplane radiator, such gauze being used on airplane models to represent the radiator" (p. 1).
Date: January 1925
Partner: UNT Libraries Government Documents Department

Hulls for Large Seaplanes

Description: "In reality, the principle of similitude is not applicable to the hulls, the designing of which increases in difficulty with increasing size of the seaplanes. In order to formulate, at least in a general way, the basic principles of calculation, we must first summarize the essential characteristics of a hull with reference to its gradual enlargement. In this study, we will disregard hulls with wing stubs, as being inapplicable to large seaplanes" (p. 2).
Date: January 1925
Creator: Magaldi, Giulio
Partner: UNT Libraries Government Documents Department

Determination of Ignition Points of Liquid Fuels Under Pressure

Description: Two series of experiments were tried, in order to determine the ignition point at any desired pressure, the first series at constant and the second at varying pressure. The results differ greatly and indicate that testing under pressure, in the investigation of liquid fuels, can be done best in the laboratory and that the determination of the ignition points in an open vessel furnishes no certain indication of the behavior of the fuel in the engine.
Date: January 1925
Creator: Tausz, J. & Schulte, F.
Partner: UNT Libraries Government Documents Department

Royal Aero Club Light Aeroplane Competition

Description: Memorandum describing the results of the Royal Aero Club light airplane competition and some of the history surrounding the event. A list of the planes that participated and an analysis of the performance of the various aircraft are provided.
Date: January 1925
Creator: Buchanan, J. S.
Partner: UNT Libraries Government Documents Department

Air flow investigation for location of angle of attack head on a JN4h airplane

Description: The technical staff of the NACA at Langley Field, has made a series of free flight tests with a JN4h airplane in order to find the best place for an instrument for measuring the angle of attack. A "neutral zone" was found where the air remains either at rest relative to the undisturbed air beyond the influence of the airplane, or is set in motion parallel to the motion of the airplane. This zone is about midway between the two wings and slightly in front of, or at the vertical plane through the leading edges of the wings but the exact position as well as the outlines of the zone varies considerably as the conditions of flight change.
Date: August 1925
Creator: Freeman, R. G.
Partner: UNT Libraries Government Documents Department

The comparison of well-known and new wing sections tested in the variable density wind tunnel

Description: Three groups of airfoils have been tested in the variable density wind tunnel. The first group contains three airfoils. The second group is a systematic series of twenty-seven airfoils. The third group consists of several frequently used wing sections.
Date: May 1925
Creator: Higgins, George J.
Partner: UNT Libraries Government Documents Department

Aircraft Engine Design

Description: From Introduction: "The subject of this paper is so broad in scope that a large volume might be devoted to it. In a short paper of this kind it is possible simply to sketch in the high lights of aircraft engine design showing the development to date, the possibilities of the future, and the underlying fundamental principles. Summarizing this development and referring to the graph (Fig.1), we that there is now a water-cooled engine in every power from 150 to 800 HP. and an air-cooled engine in the 200 to 400 HP. classes."
Date: January 1925
Creator: Wilson, E. E.
Partner: UNT Libraries Government Documents Department

The Flettner Rotor Ship in the Light of the Kutta-Joukowski Theory and of Experimental Results

Description: "In this paper the fundamental principles of the Flettner rotor ship (Reference I) are discussed in the light of the Kutta-Joukowski theory and available experimental information on the subject. A brief exposition of the Kutta-Joukowski theory is given and the speed of the rotor ship Buckau computed, first by using effective propulsive force obtained by the above theory, and then by direct application of wind tunnel data" (p. 1).
Date: October 1925
Creator: Rizzo, Frank
Partner: UNT Libraries Government Documents Department

Simplified Propeller Design for Low-Powered Airplanes

Description: "The object of this report is to furnish the designer and builder of small airplanes a simple system for designing the propeller and making the drawing. An empirical design method is used, based on tests of model propellers in a wind tunnel and full scale tests of propellers in flight. The actual designing is accomplished by means of charts and involves very little calculation" (p. 1).
Date: January 1925
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

Note on the Air Forces on a Wing Caused by Pitching.

Description: Report containing information on the air forces on a wing produced by its pitching at a finite rate of angular velocity. The condition of smooth flow at the region of the trailing edge is maintained. The wing then experiences the same lift as if moving with the momentary velocity of the rear edge.
Date: March 1925
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department

Propeller Scale Effect and Body Interference

Description: "This note shows that the main part of the discrepancy between full flight propeller performance and the performance of models in a wind tunnel is due to a scale effect, and that a minor part is caused by body interference. Analyses are made of propeller performances on several standard airplanes, and the actual brake horsepower compared with the power as calculated from model test data. The calculated power is based on that absorbed by a wind tunnel propeller model which is geometrically similar to the full scale propeller and is operating under the same ratio of V/nD" (p. 1).
Date: September 1925
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

The Estimation of Airplane Performance From Wind Tunnel Tests on Conventional Airplane Models

Description: Calculations of the magnitude of the correction factors and the range of their variations for wind tunnel models used in making aircraft performance predictions were made for 23 wind tunnel models. Calculated performances were compared with those actually determined for such airplanes as have been built and put through flight test. Except as otherwise noted, all the models have interplane struts and diagonal struts formed to streamwise shape. Wires were omitted in all cases. All the models were about 18 inches in span and were tested in a 4-foot wind tunnel. Results are given in tabular form.
Date: May 1925
Creator: Warner, Edward P. & Ober, Shatswell
Partner: UNT Libraries Government Documents Department

The Drift of an Aircraft Guided Towards It's Destination by Directional Receiving of Radio Signals Transmitted From the Ground

Description: Following a curved path increases the distance to be flown, and a type of radio navigation that forces the adoption of such a path is therefore less efficient than one that marks out a definite straight line between the point of departure and the intended destination, and holds the airplane to that line. To determine the loss of efficiency resulting from curvature of the path, calculations were made for two particular cases by the method of step-by-step integration. The calculations were based on the assumption that the pilot makes straightforward use of his radio for navigation and makes no allowance for drift.
Date: June 1925
Creator: Warner, Edward P.
Partner: UNT Libraries Government Documents Department

An Altitude Chamber for the Study and Calibration of Aeronautical Instruments

Description: "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.
Partner: UNT Libraries Government Documents Department