National Advisory Committee for Aeronautics (NACA) - 91 Matching Results

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Aerodynamic Characteristics of a 4-Engine Monoplane Showing Comparison of Air-Cooled and Liquid-Cooled Engine Installations

Description: From Introduction: "An investigation has been conducted in the N.A.C.A. full-scale wind tunnel to determine the aerodynamic characteristics of a 1/4-scale model of a 4-engine monoplane when equipped with comparable air-cooled engine and liquid-cooled engine installations. The air-cooled engine installation consisted of nacelles equipped with N..A.C.A. cowlings and oil coolers located in the leading edge of the wing."
Date: July 1939
Creator: Silverstein, Abe & Wilson, Herbert A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air forces and air-force moments at large angles of attack and how they are affected by the shape of the wing

Description: From Summary: "The present report is, in the first place, a compilation of the test results now available from wing tests up to angles of attack 90^o. Reports are also given of tests with monoplane and auxiliary wings in the Gottingen wind tunnel for the purpose of plotting a steadily rising curve of the normal force as a foundation of the angle of attack."
Date: July 1930
Creator: Fuchs, Richard & Schmidt, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airplane Landing Gear

Description: This report presents an investigation of the design and construction of various types of landing gears. Some of the items discussed include: chassises, wheels, shock absorbers (rubber disk and rubber cord), as well as oleopneumatic shock absorbers. Various types of landing gears are also discussed such as the Messier, Bendix, Vickers, and Bleriot.
Date: July 1931
Creator: Maiorca, Salvatore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The apparent width of the plate in compression

Description: This report discusses an investigation that treats the load capacity of a rectangular plate stressed in compression on one direction (x) beyond the buckling limit and the plate is rotatable (i.e., free from moments) supported at all four sides by bending-resistant beams.
Date: July 1937
Creator: Marguerre, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Behavior of a Plate Strip Under Shear and Compressive Stresses Beyond the Buckling Limit

Description: The present report is an extension of previous theoretical investigations on the elastic behavior of a plate under compression and shear in the region above the critical. The main object is the clarification of the behavior immediately above the buckling limit since no theoretical expressions for this range have thus far been found and since experimentally, too, any degree of regularity in the behavior of the plate in the range between the critical load and about three to four times the critica… more
Date: July 1938
Creator: Kromm, A. & Marguerre, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of Potential Flow Past Airship Bodies in Yaw

Description: An outline of Von Karman's method of computing the potential flow of airships in yaw by means of partially constant dipolar superposition on the axis of the body is followed by several considerations for beginning and end of the superposition. Then this method is improved by postulating a continuous, in part linearly variable dipolar superposition on the axis. The second main part of the report brings the calculation of the potential flow by means of sources and sinks, arranged on the surface o… more
Date: July 1932
Creator: Lotz, I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of Pressure Distribution on Airship Hulls

Description: These calculations were based on the shape of the ZR III, with the following simplifications: cars, fins, and rudders removed; all cross sections replaced by equivalent circular cross sections. Under these assumptions the pressure distribution was calculated for the following cases: symmetrical case, or flow parallel to the axis; unsymmetrical case, or flow at an angle to the axis. In both cases the simple potential flow first forms the basis for the determination of the pressure distribution.
Date: July 1930
Creator: Von Karman, Theodor
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Carbon-monoxide indicators for aircraft

Description: Several improvements that have been made on commercially available carbon-monoxide indicators to make them more suitable for aircraft use are described. These improvements include an automatic flow regulator, which permits the use of a simplified instrument on aircraft where a source of suction is available, and a more reliable alarm attachment. A field method for testing instruments on standard samples of carbon monoxide is described. Performance data and instructions in operation and maintena… more
Date: July 1936
Creator: Womack, S. H. J. & Peterson, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for Checking the Stability of Compression Members in Trusses

Description: "The present report contains a set of charts developed for computing the fixity effect on a compression member in a truss through its adjacent members, the amount of fixity being considered variable with the particular total truss load. The use of the charts is illustrated on two- and three-bay systems, as well as on a triangular truss" (p. 1).
Date: July 1936
Creator: Borkmann, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparative Performance of a Powerplus Vane-Type Supercharger and an N.A.C.A. Roots-Type Supercharger

Description: "This report presents the results of tests of a Powerplus supercharger and a comparison of its performance with the performance previously obtained with an N.A.C.A. Roots-type supercharger. The Powerplus supercharger is a positive displacement blower of the vane type having mechanically operated vanes, the movement of which is controlled by slots and eccentrics. The supercharger was tested at a range of pressure differences from 0 to 15 inches of mercury and at speeds from 500 to 2,500 r.p.m." … more
Date: July 1932
Creator: Schey, Oscar W. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A complete tank test of a model of a flying-boat hull - N.A.C.A. Model No. 11

Description: "This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of compari… more
Date: July 1933
Creator: Shoemaker, James M. & Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Complete Tank Test of a Model of a Flying-Boat Hull - N.A.C.A. Model No.11

Description: "This note discusses the limitations of the conventional tank test of a seaplane model. The advantages of a complete test, giving the characteristics of the model at all speeds, loads, and trim angles in the useful range are pointed out. The data on N.A.C.A. Model No.11, obtained from a complete test, are presented and discussed. The results are analyzed to determine the best trim angle for each speed and load. The data for the best angles are reduced to non-dimensional form for ease of compari… more
Date: July 1933
Creator: Shoemaker, James M. & Parkinson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Compressibility Burble and the Effect of Compressibility on Pressures and Forces Acting on an Airfoil

Description: "Simultaneous air-flow photographs and pressure-distribution measurements were made of the NACA 4412 airfoil at high speeds to determine the physical nature of the compressibility burble. The tests were conducted in the NACA 24-inch high-speed wind tunnel. The flow photographs were obtained by the Schlieren method and the pressures were simultaneously measured for 54 stations in the 5-inch-chord airfoil by means of a multiple-tube manometer. Following the general program, a few measurements of … more
Date: July 6, 1938
Creator: Stack, John; Lindsey, W. F. & Littell, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The "Comte A.C. 3" Military Airplane (Swiss) : A High-Wing Semicantilever Monoplane

Description: Circular presenting a description of the Comte A.C. 3, which is a high-wing monoplane with tow tandem 600 hp Hispano-Suiza engines mounted above the fuselage. Details of the design, fuel tanks, fuselage, pilot seating, engine, wings, safety factors, and flight qualities are provided.
Date: July 1930
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Contributions to the Theory of Incomplete Tension Bay

Description: The present report offers an approximate theory for the stress and deformation condition after buckling of the skin in reinforced panels and shells loaded in simple shear and compression and under combined stresses. The theory presents a unified scheme for stresses of these types. It is based upon the concept of a nonuniform stress distribution in the metal panel and its marked power of resistance against compressive stresses ("incomplete" tension bay).
Date: July 1937
Creator: Schapitz, E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Conversion of Energy in a Radiator

Description: It was a worthwhile task to research methods to lower the cooling drag of radiators. And the success of these efforts has been so great that without this research the modern high-speed airplane would have decidedly inferior performance. It is the purpose of this report to give a comprehensive discussion of all the fundamental principles and phenomena that offer a key to understanding modern cooling problems.
Date: July 1938
Creator: Weise, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correction of Downwash in Wind Tunnels of Circular and Elliptic Sections

Description: The downwash velocity distribution behind the wing was determined for the free jet and for the closed tunnel of both circular and elliptic cross sections. The wing was placed at the center of the tunnel. The theory makes it possible to determine the downwash at any point in the jet. The computations were performed for points in the plane determined by the jet axis and the center-of-pressure line of the wing.
Date: July 1936
Creator: Lotz, Irmgard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The critical velocity of a body towed by a cable from an airplane

Description: It is sufficient to consider only the equations of motion of the towed body whereas those of the cable may be left out of consideration. The result obtained makes it possible to determine which factors affect the critical velocity and what modifications of the instrument are necessary for extending the upper limit of that velocity.
Date: July 1937
Creator: Koning, C. & DeHaas, T. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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