National Advisory Committee for Aeronautics (NACA) - 1,270 Matching Results

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Ignition points and combustion reactions in Diesel engines. Part I

Description: The question of whether the fuel should be adapted to the engine or whether it is possible to improve equipment such as carburetors and engines so that as much of the crude oil as possible may be used without further transformation is examined in this report. Various ignition points and fuel mixtures are investigated in this regard.
Date: October 1, 1928
Creator: Tausz, J & Schulte, F
Partner: UNT Libraries Government Documents Department

Wheel brakes and their application to aircraft

Description: The advantages to be gained from braking have not been ignored, and in the search for a suitable method many schemes have been suggested and tried. Some of the methods discussed in this paper include: 1) increasing the height of the landing gear; 2) air brakes of various forms; 3) sprags on tail skid and axle; and 4) wheel brakes. This report focuses on the design of wheel brakes and wheel brake controls.
Date: May 1, 1928
Creator: Dowty, G H
Partner: UNT Libraries Government Documents Department

The 1926 German seaplane contest

Description: The report discusses the problem of rating the various seaplane designs from the 1926 seaplane contest. The whole process of rating consists in measuring the climbing speed, flying weight and carrying capacity of a seaplane and then using these data as the basis of a construction problem.
Date: March 1928
Creator: Seewald, F; Blenk, H & Liebers, F
Partner: UNT Libraries Government Documents Department

Calculation of Airplane Performances Without the Aid of Polar Diagrams

Description: For good profiles the profile-drag coefficient is almost constant in the whole range which comes into consideration for practical flight. This is manifest in the consideration of the Gottingen airfoil tests and is confirmed by the investigations of the writer (measurements of the profile drag during flight by the Betz method), concerning which a detailed report will soon be published. The following deductions proceed from this fact. The formulas developed on the assumptions of a constant profile-drag coefficient afford an extensive insight into the influences exerted on flight performances by the structure of the airplane.
Date: March 1, 1928
Creator: Schrenk, Martin
Partner: UNT Libraries Government Documents Department

Choice of profile for the wings of an airplane. Part I

Description: The choice of the profile for the wings of an airplane is a problem which should be solved by a scientific method based on data obtained by systematic experimentation. The problem, in its present form, may be stated as follows: "To find a profile which has certain required aerodynamic characteristics and which encloses the spars, whose number, dimensions and separating distance are likewise determined by structural considerations." At present, the static test, corresponding to the case of accelerated flight at limited speed, requires the knowledge of the moment of the aerodynamic resultant at the angle of zero lift, and the possibility of controlling the magnitude of the corresponding absolute coefficient within more or less extensive limits.
Date: June 1, 1928
Creator: Toussaint, A & Carafoli, E
Partner: UNT Libraries Government Documents Department

Safety in airplane flight

Description: This report presents methods to reduce the incidence of aviation accidents. Some of the methods discussed include enlistment and training of aviators, improvement of controls and control surfaces, and upgrading of power plants.
Date: November 1, 1927
Creator: Brunat, H
Partner: UNT Libraries Government Documents Department

"Gloster" high lift biplane wings

Description: The main object of these wings was to obtain a high lift without increasing the total drag, and the idea was conceived that, by using a deep high-lift section for the top wing and a medium section for the bottom wing, the mutual interference between the two would be such as to give greater efficiency of the combination as compared with two wings of equal section.
Date: December 1, 1927
Creator: Preston, H E
Partner: UNT Libraries Government Documents Department

Duralumin - defects and failures

Description: It is proposed in this paper to identify some of the defects and failures in duralumin most frequently encountered by the aircraft industry with a view to indicate their importance. The defects and failures in duralumin may be classified into the following groups: 1) defects produced during manufacture; 2) defects produced during fabrication; 3) corrosion and erosion; and 4) fatigue failures. Only the first two will be covered in this report.
Date: December 1, 1927
Creator: Nelson, WM
Partner: UNT Libraries Government Documents Department

Experiments on airfoils with aileron and slot

Description: The present report contains the results of a few experiments on three airfoils to which the rear portions, having chords respectively 1/4, 1/3, and 2/5 of the total chords, are hinged so as to form ailerons, especial attention being given to the shape of the slot between the aileron and the main portion of the aileron.
Date: November 1927
Creator: Betz, A.
Partner: UNT Libraries Government Documents Department

Aviation fuels : with especial reference to "white spirit."

Description: Gasoline, the fuel now used, is an extremely volatile and inflammable liquid capable of forming explosive mixtures, the cause of many catastrophes in aviation. It is therefore of special interest to investigate the possibility of using fuels which, while being less volatile than gasoline, would nevertheless enable this engine to function satisfactorily.
Date: February 1928
Creator: Dumanois, P
Partner: UNT Libraries Government Documents Department

Motion of fluids with very little viscosity

Description: Report presenting a discussion of the laws of motion of a fluid with very low viscosity. Mathematical formulas that have been created in order to compensate for this lack of viscosity and the circumstances under which viscosity can be disregarded are provided.
Date: March 1928
Creator: Prandtl, L.
Partner: UNT Libraries Government Documents Department

Experiments with a wing from which the boundary layer is removed by pressure or suction

Description: With an unsymmetrical wing and a rotating Magnus cylinder, the lift is produced by the superposition of parallel and circulatory flows. An explanation of the circulatory flow is furnished by the boundary-layer theory of Prandtl and the consequent vortex formation. According to this explanation, it must evidently be possible to increase the circulation either by increasing the size of the stronger (lower) vortex or by decreasing the size of the weaker (upper) vortex. In this sense, according to Professor H. Zickendraht, we have a new type of wing from which the boundary layer is removed by forcing air out or sucking it in through openings in the upper surface of the wing near its trailing edge.
Date: July 1, 1928
Creator: Wieland, K
Partner: UNT Libraries Government Documents Department

The span as a fundamental factor in airplane design

Description: Previous theoretical investigations of steady curvilinear flight did not afford a suitable criterion of "maneuverability," which is very important for judging combat, sport and stunt-flying airplanes. The idea of rolling ability, i.e., of the speed of rotation of the airplane about its X axis in rectilinear flight at constant speed and for a constant, suddenly produced deflection of the ailerons, is introduced and tested under simplified assumptions for the air-force distribution over the span. This leads to the following conclusions: the effect of the moment of inertia about the X axis is negligibly small, since the speed of rotation very quickly reaches a uniform value.
Date: September 1, 1928
Creator: Lachmann, G
Partner: UNT Libraries Government Documents Department

Considerations on propeller efficiency

Description: The propeller cannot be considered alone, but the mutual interference between propeller and airplane must be considered. These difficulties are so great when the joint action of propeller and airplane is considered, that the aerodynamic laboratory at Gottingen originally abandoned the idea of applying the efficiency conception of the test results. These difficulties and the methods by which they are overcome are outlined in this report.
Date: September 1928
Creator: Betz, A.
Partner: UNT Libraries Government Documents Department

Determination of the air forces and moments produced by the ailerons of an airplane

Description: As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distribution, so that an approximate evaluation of the distribution may be regarded as satisfactory. After a few brief remarks on the fundamentals of the exact computation, the method will be so presented that the lift distribution for deflected ailerons may be determined for other values of the parameter p from the results already obtained. Coefficients will then be given in the form of diagrams and numerical tables, from which the desired forces and moments can be easily obtained by substitution in the given equations.
Date: November 1, 1928
Creator: Wieselberger, C & Asano, T
Partner: UNT Libraries Government Documents Department

Influence of fuselage on propeller design

Description: In the present paper I shall not consider the problem of the best arrangement of airplane and propeller, but only a simple method for designing a propeller for a given arrangement of airplane parts. The inflow to the propeller and hence the efficiency of the propeller is affected most by the fuselage.
Date: December 1, 1928
Creator: Troller, Theodor
Partner: UNT Libraries Government Documents Department

Mechanical properties of some materials used in airplane construction

Description: Since lightness is desirable in airplane construction, greater stresses must be tolerated than in other kinds of construction. It is therefore necessary to have a more accurate knowledge of the greatest stresses that may occur and of the actual properties of the materials used. The Aeronautic Research Laboratories took the limit of elasticity as the basis of the strength calculations. Many tests were made of different steels, woods, aluminum alloys, and fabrics.
Date: January 1, 1928
Creator: Wolff, E B & Van Ewijk, L J G
Partner: UNT Libraries Government Documents Department

Welding in airplane construction

Description: The present article attempts to explain the principles for the production of a perfect weld and to throw light on the unexplained problems. Moreover, it is intended to elucidate the possibilities of testing the strength and reliability of welded parts.
Date: February 1, 1928
Creator: Rechtlich, A & Schrenk, M
Partner: UNT Libraries Government Documents Department

Systematic investigation of Joukowsky wing sections

Description: Ackeret began systematic polar measurements on Joukowsky wing sections, which were occasionally conducted in the wind tunnel. Under these conditions a considerable number of wing sections were tested during the last four years and the tests are now more or less concluded.
Date: July 1, 1927
Creator: Schrenk, O
Partner: UNT Libraries Government Documents Department