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

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The problem of fuel measurement : the Schiske "Konsummeter"

Description: Any measuring device, which immediately indicates the rate of fuel consumption in the desired units, has the advantage of saving considerable time and fuel, besides facilitating the adjustment of the carburetor. The Schiske "Konsummeter" (made by the "PS-Vergaser and Apparatebau A. G.") was designed from the above viewpoint.
Date: May 1, 1925
Creator: Praetorius, K. R. H.
Partner: UNT Libraries Government Documents Department

Air forces on airfoils moving faster than sound

Description: We are undertaking the task of computing the air forces on a slightly cambered airfoil in the absence of friction and with an infinite aspect ratio. We also assume in advance that the leading edge is very sharp and that its tangent lies in the direction of motion.
Date: June 1925
Creator: Ackeret, J
Partner: UNT Libraries Government Documents Department

The light airplane: modern theoretical aerodynamics as applied to light airplane design with a series of charts

Description: T.M. 311 gave a short outline of modern theoretical aerodynamics as applied to light airplane design. This discussion may have been somewhat obscure to the nontechnical reader. A series of charts or curves should serve to clear up such obscurity as well as to more definitely emphasize those quantities most important for each flight characteristic.
Date: August 1, 1925
Creator: Driggs, Ivan H.
Partner: UNT Libraries Government Documents Department

The Light Airplane

Description: This report begins with a review and analysis of the work being done to develop light airplanes in the U.S. and abroad. A technical discussion of the construction and innovations in light airplanes is then presented.
Date: April 1925
Creator: Driggs, Ivan H.
Partner: UNT Libraries Government Documents Department

Astronomical methods in aerial navigation

Description: The astronomical method of determining position is universally used in marine navigation and may also be of service in aerial navigation. The practical application of the method, however, must be modified and adapted to conform to the requirements of aviation. Much of this work of adaptation has already been accomplished, but being scattered through various technical journals in a number of languages, is not readily available. This report is for the purpose of collecting under one cover such previous work as appears to be of value to the aerial navigator, comparing instruments and methods, indicating the best practice, and suggesting future developments. The various methods of determining position and their application and value are outlined, and a brief resume of the theory of the astronomical method is given. Observation instruments are described in detail. A complete discussion of the reduction of observations follows, including a rapid method of finding position from the altitudes of two stars. Maps and map cases are briefly considered. A bibliography of the subject is appended.
Date: 1925
Creator: Beij, K. Hilding
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.
Date: January 1, 1925
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. The last advance included in the wing section was an increase in wing area by means of an auxiliary wing adjusted by a sort of rectangular joint.
Date: January 1, 1925
Creator: Lachmann, G
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 1, 1925
Creator: Tausz, J & Schulte, F
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.
Date: January 1, 1925
Creator: Magaldi, Giulio
Partner: UNT Libraries Government Documents Department

Determination and classification of the aerodynamic properties of wing sections

Description: The following note, prepared for the NACA, contains several remarks on the possible improvement of the experimental determination of the aerodynamic properties of wing sections. It shows how errors of observation can subsequently be partially eliminated, and how the computation of the maxima or minima of aerodynamic characteristics can be much improved.
Date: September 1, 1925
Creator: Munk, Max M.
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.
Date: October 1, 1925
Creator: Rizzo, Frank
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 1, 1925
Creator: Wilson, E E
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. Results obtained with this chamber have a direct application in the design and calibration of instruments used in free flight research.
Date: November 1925
Creator: Reid, J E & Kirchner, Otto E
Partner: UNT Libraries Government Documents Department

The velocity distribution caused by an airplane at the points of a vertical plane containing the span

Description: A formula for the computation of the vertical velocity component on all sides of an airplane is deduced and discussed. The formation is of value for the interpretation of such free flight tests where two airplanes fly alongside each other to facilitate observation.
Date: March 1, 1925
Creator: Munk, Max M.
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.
Date: January 1, 1925
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

Note on the air forces on a wing caused by pitching.

Description: The following contains information on the air forces on a wing produced by it's 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 1, 1925
Creator: Munk, Max M.
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 1, 1925
Creator: Warner, Edward P. & Ober, Shatswell
Partner: UNT Libraries Government Documents Department

Pressure distribution on the nose of an airship in circling flight

Description: In recent tests on the pressures occurring on the envelope and control surfaces of the naval airship C-7, it was noted that the pressures on the nose of the airship, while flying in level circling flight, were symmetrically distributed. Such a condition can only occur when the nose of the airship is pointed directly into the wind, and to accomplish this in circling flight, the axis of the airship must then be parallel to the direction of the motion of the nose. The question was raised as to whether the same conditions occur generally on all airships in circling flight. It appears that airships flying in a constant, level, circling flight path will generally head very closely into the wind, and any deviation will be so slight that the distribution of pressure over the nose will be but slightly, if at all, changed from a symmetrical distribution.
Date: August 1, 1925
Creator: Fairbanks, Karl J
Partner: UNT Libraries Government Documents Department