National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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General Biplane Theory

Description: "This report deals with the air forces on biplane cellule. The first part of the report deals with the two-dimensional problem neglecting viscosity. The second part deals with the influence of the lateral dimensions. It is found that the loss of lift due to induction is almost unchanged, whether the biplane is staggered or not. In the third part conclusions from previous investigations are drawn, viscosity and experimental experience are brought in, and the method is simplified for practical ap… more
Date: 1923
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The general efficiency curve for air propellers

Description: This report presents a formula which may be used to obtain a "general efficiency curve" in addition to the well-known maximum efficiency curve. These two curves, when modified somewhat by experimental data, enable performance calculations to be made without detailed knowledge of the propeller. The curves may also be used to estimate the improvement in efficiency due to reduction gearing, or to judge the performance of a new propeller design.
Date: 1923
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General Theory of Thin Wing Sections

Description: "This report contains a new, simple method of calculating the air forces to which thin wings are subjected at small angles of attack, if their curvature is not too great. Two simple integrals are the result. They contain only the coordinates of the wing section" (p. 3).
Date: 1923
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Internal Stresses in Laminated Construction

Description: "This report reviews the procedure employed in an investigation of the sources and influence of internal stresses in laminated construction, and discusses the influence of shrinkage and swelling stresses caused by atmospheric conditions upon the tensile strength across grain in laminated construction with special reference to airplane propellers. The investigation covered three sources of internal stress, namely, the combination of plain-sawed and quarter-sawed material in the same construction… more
Date: 1923
Creator: Heim, A. L.; Knauss, A. C. & Seutter, Louis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift and Drag Effects of Wing-Tip Rake

Description: This report deals with a description and report of tests carried out at the Washington Navy Yard on models of the RAF-6, albatross and Slone airfoils to determine the effectiveness of the conventional wing-trailing edge being always longer than the leading edge. The results are compared with the values computed by standard formulae in use at the time the tests were conducted.
Date: 1923
Creator: Zahm, A. F.; Bear, R. M. & Hill, G. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Marcel Besson Wing Sections

Description: Three different Marcel Besson airfoils are investigated in terms of maximum lift, maximum fineness, minimum required power, and wing section drag. Comparisons are then made between the three airfoils.
Date: January 1923
Creator: Delanghe, C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Mathematical Equations for Heat Conduction in the Fins of Air-Cooled Engines

Description: The problem considered in this report is that of reducing actual geometrical area of fin-cooling surface, which is, of course, not uniform in temperature, to equivalent cooling area at one definite temperature, namely, that prevailing on the cylinder wall at the point of attachment of the fin. This makes it possible to treat all the cooling surface as if it were part of the cylinder wall and 100 per cent effective. The quantities involved in the equations are the geometrical dimensions of the f… more
Date: 1923
Creator: Harper, D. R. & Brown, W. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Minimum Induced Drag of Aerofoils

Description: This report helps explain the phenomenon of flight. It contains some theorems concerning the arrangement of airplane wings which are of considerable practical interest. In particular, it shows the theoretical reasons for the decrease of drag which accompanies all increase in the aspect ratio or lateral extension of a wing. The efficiency of a given arrangement of wings may be calculated from the formulae derived in this paper.
Date: 1923
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Nomenclature for Aeronautics

Description: "This nomenclature for aeronautics was prepared by a special conference on aeronautical nomenclature, composed of representatives of the Army and Navy Air Services, the Air Mail Service, the Bureau of Standards, the National Advisory Committee for Aeronautics, and private life. This report supersedes all previous publications of the committee on this subject. It is published with the intention of securing greater uniformity and accuracy in official documents of the government, and, as far as po… more
Date: 1923
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Optical Altitude Indicator for Night Landing

Description: One of the most ingenious of the devices intended for use in night landing, especially emergency landing, is a very simple optical instrument known as the Jenkins night altitude indicator. The design and operation of this instrument, which allows a pilot to determine the altitude of the aircraft, is discussed. The author discusses various modifications and improvements that might be made to the instrument.
Date: January 1923
Creator: Warner, John A. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Maybach 300-horsepower airplane engine

Description: "This report contains the results of a test made upon a Maybach Engine in the altitude chamber of the Bureau of Standards, where controlled conditions of temperature and pressure can be made the same as those of the desired altitude. The results of this test lead to the following conclusions: from the standpoint of thermal efficiency the full-load performance of the engine is excellent at densities corresponding to altitudes up to and including 15,000 feet. The brake mean effective pressure is … more
Date: 1923
Creator: Sparrow, S. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Point drag and total drag of navy struts no. 1 modified

Description: This report deals with the results of tests on struts conducted at Washington Navy Yard. Two models of the modified Navy strut, no. 1, were tested in the 8 by 8 foot wind tunnel. The tests were made to determine the total resistance end effect and the pressure distribution at various wind-tunnel speeds with the length of the strut transverse to the current. Only the measurements made at zero pitch and yaw are given in this report.
Date: 1923
Creator: Zahm, A. F.; Smith, R. H. & Hill, G. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Possible Improvements in Gasoline Engines

Description: High-compression engines are investigated with the three main objects being elimination of vibration, increase of maximum efficiency, and conservation of this efficiency at the highest possible speeds.
Date: January 1923
Creator: Ziembinski, S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Practical Stability and Controllability of Airplanes

Description: "The effect of the characteristics of an airplane on balance, stability, and controllability, based on free flight tests, is discussed particularly in respect to the longitudinal motion. It is shown that the amount of longitudinal stability can be varied by changing the position of the center of gravity or by varying the aspect ratio of the tail plane, and that the stability for any particular air speed can be varied by changing the camber of the tail plane. It is found that complete longitudin… more
Date: 1923
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Pressure Distribution Over the Horizontal Tail Surfaces of an Airplane

Description: "This work was undertaken to determine as completely as possible the distribution of pressure over the horizontal tail surfaces of an airplane, and to analyze the relation of this pressure to the structural loads and the longitudinal stability. The investigation is divided into three parts, of which this the first. The first part of the investigation is for the purpose of determining the pressure distribution over two horizontal tail surfaces in uniform free flight; the second part to conduct t… more
Date: 1923
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Pressure Distribution Over the Horizontal Tail Surfaces of an Airplane 3

Description: This report contains the results of an investigation of the distribution of pressure over the tail surfaces of a full-sized airplane during accelerated flight for the purpose of determining the magnitude of the tail and fuselage stresses in maneuvering. As the pressures in accelerated flight change in value with great rapidity, it was found that the liquid manometer used in the first part of this investigation would not be at all suitable under these conditions; so it was necessary to design an… more
Date: 1923
Creator: Norton, F. H. & Brown, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Distribution Over the Rudder and Fin of an Airplane in Flight

Description: "This investigation was carried out by the National Advisory Committee for Aeronautics at the Langley Memorial Aeronautical Laboratory for the purpose of determining the loads which occur on the vertical tail surfaces in flight. The method consisted in measuring the pressures simultaneously at 28 points on the rudder and fin by means of a recording multiple manometer. The results show that the maximum load encountered in stunting was 7 pounds per square foot on the rudder and fin, and it is pro… more
Date: 1923
Creator: Norton, F. H. & Brown, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure distribution over thick airfoils - model tests

Description: From Summary: "This investigation was undertaken to study the distribution of loading over thick wings of various types. The unloading on the wing was determined by taking the pressure at a number of holes on both the upper and lower surfaces of a model wing in the wind tunnel. The results from these tests show, first, that the distribution of pressure over a thick wing of uniform section is very little different from that over a thin wing; second, that wings tapering either in chord or thickne… more
Date: 1923
Creator: Norton, F. H. & Bacon, D. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Results of experimental flights at high altitudes with Daimler, Benz and Maybach engines to determine mixture formation and heat utilization of fuel

Description: The experimental flights described herein were made with the object of obtaining information regarding the following two questions, which as yet have not been sufficiently elucidated. These are: 1. What effect has altitude upon the formation of the mixture? 2. What alteration takes place, with increasing altitude, in the utilization of the heat contained in the fuel?.
Date: January 1923
Creator: Kutzbach, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Simplified theory of the magneto

Description: From Summary: "This paper contains part of the results of ignition investigations being made for the National Advisory Committee for Aeronautics at the Bureau of Standards, and describes a type of circuit which has been found useful for representing the action of high-tension magneto. While this equivalent circuit is relatively simple, and consequently can be used as a basis for deriving definite mathematical formulas for induced voltages and similar quantities, it has been found experimentally… more
Date: 1923
Creator: Silsbee, F. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The six-component wind balance

Description: Dr. Zahm's report is a description of the six-component wind-tunnel balance in use at the Aerodynamic Laboratory, Washington Navy Yard. The description of the balance gives the mechanical details and the method of operation, and is accompanied by line drawings showing the construction of the balance. The balance is of particular interest, as it allows the model to be set up quickly and accurately in roll, pitch, and yaw, without stopping the wind. It is possible to measure automatically, direct… more
Date: 1923
Creator: Zahm, A. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Soaring flight and the Rhön contests

Description: Explanation of soaring flight. Static and dynamic soaring flight. Results of the Rhon contest. Description of the most important gliders. Notes on Soaring Flight Contests in France and England.
Date: January 1923
Creator: Hoff, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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