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Influence of Struts and Stays on the Speed of an Airplane

Description: Report presenting an experiment in the Rechlin airdrome in the fall of 1918 to determine the influence of struts and stays on the speed of an airplane. Results indicated that only a slight increase in horizontal speed was shown in a stayless airplane, but it had considerably greater climbing speed.
Date: October 1921
Creator: Heidelberg, V.
Partner: UNT Libraries Government Documents Department
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Some Remarks Concerning Soaring Flight

Description: The publication of the following details is due to the desire of the editor to have the problems of soaring flight treated on the occasion of the Rhone Soaring Flight Contest. Soaring flight is defined as motorless flight without loss of height. Some calculations are provided in order to maximize the potential effects of wind and air currents.
Date: October 1921
Creator: Prandtl, L.
Partner: UNT Libraries Government Documents Department
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Crippling Strength of Axially Loaded Rods

Description: A new empirical formula was developed that holds good for any length and any material of a rod, and agrees well with the results of extensive strength tests. To facilitate calculations, three tables are included, giving the crippling load for solid and hollow sectioned wooden rods of different thickness and length, as well as for steel tubes manufactured according to the standards of Army Air Services Inspection. Further, a graphical method of calculation of the breaking load is derived in which a single curve is employed for determination of the allowable fiber stress.
Date: October 1921
Creator: Natalis, F. & Pawlowski, F. W.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. Recording Air Speed Meter

Description: A new type of air speed meter is described which was designed by the technical staff of the National Advisory Committee for Aeronautics. The instrument consists essentially of a tight metal diaphragm of high natural period which is acted upon by the pressure difference of a pitot-static head. The resulting deflection of this diaphragm is recorded optically on a moving film.
Date: October 1921
Creator: Norton, F. H.
Partner: UNT Libraries Government Documents Department
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Graphic Method for Calculating the Speed and Climbing Ability of Airplanes

Description: Note presenting a graphic method for calculating the speed and climbing ability of airplanes. This method starts from the actual power developed by the engine and makes it possible to determine all factors which together constitute what are known as flight performances for any combination of engine and airplane from the single graphic diagram given.
Date: October 1923
Creator: Rohrbach, Adolf & Lupberger, Edwin
Partner: UNT Libraries Government Documents Department
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General Theory of Windmills

Description: In this paper the application of the slip curve method to the design and analysis of windmills is discussed and illustrated by example.
Date: October 1923
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department
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The Logarithmic Polar Curve - Its Theory and Application to the Predetermination of Airplane Performance

Description: "The logarithmic polar curve has for several years been used by the most prominent aerodynamical laboratories as well as by airplane manufacturers in Europe. To show more clearly the practical application of the polar curve, a series of examples are given with suggestions for solution. After a discussion of the theory and the practical application of the polar curve, the following problems are discussed: climbing flight, speed at various altitudes, and the characteristics of two seater observation airplanes of recent design" (p. 1).
Date: October 1924
Creator: Cronstedt, Val
Partner: UNT Libraries Government Documents Department
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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
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The Arithmetic of Distribution in Multi-Cylinder Engines

Description: Note presenting a consideration of the effect on engine performance of a known inequality of distribution. A measure of perfect distribution is provided and some of the factors that influence the unequal distribution of power among cylinders.
Date: October 1923
Creator: Sparrow, Stanwood W.
Partner: UNT Libraries Government Documents Department
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Pressure distribution on wing ribs of the VE-7 and TS airplanes in flight

Description: This paper is the first of a series of notes, each of which presents the complete results of pressure distribution tests made by the National Advisory Committee for Aeronautics, on single-wing ribs of the VE-7 and TS airplanes for a particular condition of flight. The level flight results are presented here in the form of curves and show the comparison between the pressure distribution over a representative thin wing, R.A.F.-15, and a moderately thick wing, U.S.A.-27, throughout the range of angle of attack.
Date: October 1927
Creator: Rhode, R. V.
Partner: UNT Libraries Government Documents Department
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Mass distribution and performance of free flight models

Description: This note deals with the mass distribution and performance of free flight models. An airplane model which is to be used in free flight tests must be balanced dynamically as well as statically, e.g., it must not only have a given weight and the proper center of gravity but also a given ellipsoid of inertia. Equations which relate the motions of an airplane and its model are given. Neglecting scale effect, these equations may be used to predict the performance of an airplane, under the action of gravity alone, from data obtained in making dropping tests of a correctly balanced model.
Date: October 1927
Creator: Scherberg, Max & Rhode, R. V.
Partner: UNT Libraries Government Documents Department
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The effect of longitudinal moment of inertia upon dynamic stability

Description: "Free flight tests were carried out to show whether the longitudinal oscillations of a standard S.E.5A airplane are noticeably affected if its longitudinal moment of inertia is increased. These oscillations were taken by means of a self-recording instrument, the airplane having first its ordinary moment of inertia and then one increased by 14 percent. The period of oscillation was slightly longer after the increase of the moment of inertia, but the damping was not affected" (p. 1).
Date: October 1922
Creator: Norton, F. H. & Carroll, T.
Partner: UNT Libraries Government Documents Department
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Tests of the Daimler D-IVa Engine at a High Altitude Test Bench

Description: Reports of tests of a Daimler IVa engine at the test-bench at Friedrichshafen, show that the decrease of power of that engine, at high altitudes, was established, and that the manner of its working when air is supplied at a certain pressure was explained. These tests were preparatory to the installation of compressors in giant aircraft for the purpose of maintaining constant power at high altitudes.
Date: October 1920
Creator: Noack, W. G.
Partner: UNT Libraries Government Documents Department
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Notes on Specifications for French Airplane Competitions

Description: Given here are the rules officially adopted by the Aeronautical Commission of the Aero Club of France for a flight competition to be held in France in 1920 at the Villacoublay Aerodrome. The prize will be awarded to the pilot who succeeds in obtaining the highest maximum and lowest minimum speeds, and in landing within the shortest distance.
Date: October 1920
Creator: Margoulis, W.
Partner: UNT Libraries Government Documents Department
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F-5-L boat seaplane: Comparative performance with direct and geared engines

Description: Comprehensive tests were made to compare the performance of the F-5-L Boat Seaplane fitted with direct drive and Liberty engines. Details are given on the test conditions. The conclusions of the comparison tests follow. 1) An F-5-L with geared engines takes off in approximately 90 percent of the time required for the same airplane with standard direct drive engines. An F-5-L with geared engines climbs in 20 minutes to an altitude approximately 20 percent greater than that obtained with the standard direct drive on the same airplane.
Date: October 1922
Creator: Diehl, W. S.
Partner: UNT Libraries Government Documents Department
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The Synchronization of NACA Flight Records

Description: "A method is described for synchronizing the different instrument records taken during flight testing. This method has been in use for sometime at the Langley Memorial Aeronautical Laboratory and has proved very valuable in connection with the study of controllability and other complicated problems of flight" (p. 1).
Date: October 1922
Creator: Brown, W. G.
Partner: UNT Libraries Government Documents Department
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Langley Field wind tunnel apparatus

Description: From Summary: "The difficulties experienced in properly holding thin tipped or tapered airfoils while testing on an N.P.L. type aerodynamic balance even at low air speeds, and the impossibility of holding even solid metal models at the high speeds attainable at the National Advisory Committee's wind tunnel, necessitated the design of a balance which would hold model airfoils of any thickness and at speeds up to 150 m.p.h. In addition to mechanical strength and rigidity, it was highly desirable that the balance readings should require a minimum amount of correction and mathematical manipulation in order to obtain the lift and drag coefficients and the center of pressure. The balance described herein is similar to one in use at the University of Gottingen, the main difference lying in the addition of a device for reading the center of pressure directly, without the necessity of any correction whatsoever. Details of the design and operation of the device are given."
Date: October 1921
Creator: Bacon, D. L.
Partner: UNT Libraries Government Documents Department
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Aneroid investigations in Germany

Description: Report presenting an experiment of aneroid development and a theoretical study of the equilibrium of forces acting on the vacuum box.
Date: October 1921
Creator: Hersey, M. D.
Partner: UNT Libraries Government Documents Department
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The N.A.C.A. Three Component Accelerometer

Description: "A new instrument known as the NACA three component accelerometer is described in this note. This instrument was designed by the technical staff of the NACA for recording accelerations along three mutually perpendicular axes, and is of the same type as the NACA single component accelerometer with the addition of two springs and a few minor improvements such as a pump for filling the dash-pots and a convenient method for aligning the springs. This note includes a few records as well as photographs of the instrument itself" (p. 1).
Date: October 1922
Creator: Reid, H. J. E.
Partner: UNT Libraries Government Documents Department
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Fittings and Other Structural Parts of Airplanes

Description: "The strength and reliability of airplanes depend greatly on the careful design and manufacture of fittings, couplings, and other highly stressed parts. The more important parts of the airplane must be occasionally tested for increased loads and in order to avoid the possibility of defects creeping in during subsequent production. Strength tests are discussed for fittings for wing spar joints, fittings for strut connections, internal bracing, control gear, and landing gear" (p. 1).
Date: October 1923
Creator: Eydam, P.
Partner: UNT Libraries Government Documents Department
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Preliminary Study of the Damping Factor in Roll

Description: This paper constitutes a general theoretical discussion of the damping factor in roll, together with the results of wind tunnel tests on the continuous rolling of U.S.A. 30 airfoil.
Date: October 1923
Creator: Shoemaker, James M. & Lee, John G.
Partner: UNT Libraries Government Documents Department
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F-5-L Boat Seaplane: performance characteristics

Description: Performance characteristics for the F-5-L Boat Seaplane are given. Characteristic curves for the RAF-6 airfoil and the F-5-L wings, parasite resistance and velocity data, engine and propeller characteristics, effective and maximum horsepower, and cruising performance are discussed.
Date: October 1922
Creator: Diehl, W. S.
Partner: UNT Libraries Government Documents Department
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Pressure Distribution on Joukowski Wings

Description: The hydrodynamics and mathematical models as applied to the potential flow about a Joukowski wing are presented.
Date: October 1925
Creator: Blumenthal, Otto & Trefftz, E.
Partner: UNT Libraries Government Documents Department
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