National Advisory Committee for Aeronautics (NACA) - 45 Matching Results

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Diaphragms for Aeronautic Instruments

Description: This investigation was carried out at the request of the National Advisory Committee for Aeronautics and comprises an outline of historical developments and theoretical principles, together with a discussion of expedients for making the most effective use of existing diaphragms actuated by the hydrostatic pressure form an essential element of a great variety instruments for aeronautic and other technical purposes. The various physical data needed as a foundation for rational methods of diaphrag… more
Date: 1923
Creator: Hersey, M. D.
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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The Tail Plane

Description: This report deals with the calculation of the equilibrium, statistical stability, and damping of the tail plane. The author has simplified the present theory of longitudinal stability for the particular purpose of obtaining one definite coefficient characteristics of the effect of the tail plane. This coefficient is obtained by substituting certain aerodynamic characteristics and some dimensions of the airplane in a comparatively simple mathematical expression.
Date: 1923%
Creator: Munk, Max M.
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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Damping Coefficients Due to Tail Surfaces in Aircraft

Description: "The object of the investigation described in this report was to compare the damping coefficients of an airfoil as calculated from a knowledge of the static characteristics of the section with those obtained experimentally with an oscillation. The damping coefficients as obtained, according to the conventional notation, can be considered either as due to pitching or as due to yawing, the oscillation in these experiments being so arranged that the surfaces oscillate about a vertical axis. This i… more
Date: January 1, 1923
Creator: Chu, Lynn
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The drag of C class airship hull with varying length of cylindric midships

Description: A model of the C class airship hull, when severed at its major section and provided with a cylindric mid-body of variable length, had its air resistance increased about in proportion to the length of the mid-body up to 3 diameters, and in about the manner to be expected from the increase of skin friction on this variable length. For greater length the drag increased less and less rapidly.
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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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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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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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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Experimental Research on Air Propellers, 5

Description: In previous reports on experimental research on air propellers, by W. F. Durand and E. P. Lesley, as contained in the National Advisory Committee for Aeronautics reports nos. 14, 30, and 64, the investigations were made progressively and each without reference to results given in preceding reports and covering only information relating to forms perhaps adjacent in geometrical form and proportion. This report is a review of the entire series of results of the preceding reports with a view of exa… more
Date: 1923
Creator: Durand, W. F. & Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Decay of a Simple Eddy

Description: The principal result obtained in this report is a generalization of Taylor's formula for a simple eddy. The discussion of the properties of the eddy indicates that there is a slight analogy between the theory of eddies in a viscous fluid and the quantum theory of radiation. Another exact solution of the equations of motion of viscous fluid yields a result which reminds one of the well-known condition for instability in the case of a horizontally stratified atmosphere.
Date: 1923
Creator: Bateman, H.
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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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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Standard Atmosphere

Description: This report was prepared at the request of the National Advisory Committee for Aeronautics and discusses the need of a standard set of values of pressure, temperature and density at various altitudes and points out the desirability of adopting such values as are most in accord with actual average conditions, in order that corrections in individual cases may be as small as possible. To meet this need, so far as the united states is concerned, all free-air observations obtained by means of kites … more
Date: 1923
Creator: Gregg, Willis Ray
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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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 Aerodynamic Properties of Thick Airfoils 2

Description: "This investigation is an extension of NACA report no. 75 for the purpose of studying the effect of various modifications in a given wing section, including changes in thickness, height of lower camber, taper in thickness, and taper in plan form with special reference to the development of thick, efficient airfoils. The method consisted in testing the wings in the NACA 5-foot wind tunnel at speeds up to 50 meters (164 feet) per second while they were being supported on a new type of wire balanc… 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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Bending moments, envelope, and cable stresses in non-rigid airships

Description: This report describes the theory of calculating the principal stresses in the envelope of a nonrigid airship used by the Bureau of Aeronautics, United States Navy. The principal stresses are due to the gas pressure and the unequal distribution of weight and buoyancy, and the concentrated loads from the car suspension cables. The second part of the report deals with the variations of tensions in the car suspension cables of any type of airship, with special reference to the rigid type, due to th… more
Date: January 1923
Creator: Burgess, C. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Applications of Modern Hydrodynamics to Aeronautics

Description: The report gives, rather briefly, in part one an introduction to hydrodynamics which is designed to give those who have not yet been actively concerned with this science such a grasp of the theoretical underlying principles that they can follow the subsequent developments. In part two there follows a separate discussion of the different questions to be considered, in which the theory of aerofoils claims the greatest portion of the space. The last part is devoted to the application of the aerofo… more
Date: 1923
Creator: Prandtl, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Drag of Zeppelin Airships

Description: This report is a discussion of the results of tests with Zeppelin airships, in which the propellers were stopped as quickly as possible while the airship was in full flight. In this paper the author refers to the theory involved in these tests and calls attention to one scientifically interesting fact which can be derived from the tests and which has not yet been noted. The most important question concerning the tests is: does the negative acceleration of an airship with stopped propellers supp… 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 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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