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  • Other Sources  (1,429)
  • NASA Technical Reports  (1,429)
  • 1940-1944  (1,429)
Collection
  • Other Sources  (1,429)
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Keywords
Years
Year
  • 1
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    Calculated and Measured Turning Performance of a Navy F2A-3 Airplane as Affected by the Use of Flaps (1943)
    In:  CASI
    Details
    Publication Date: 2019-11-26
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-ACR-3I30 , NACA-WR-W-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Preliminary Tests in the NACA Tank to Investigate the Fundamental Characteristics of Hydrofoils (1940)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: This preliminary investigation was made to study the hydrodynamic properties and general behavior of simple hydrofoils. Six 5- by 30-inch plain, rectangular hydrofoils were tested in the NACA tank at various speeds, angles of attack and depths below the water surface. Two of the hydrofoils had sections representing the sections of commonly used airfoils, one had a section similar to one developed Guidoni for use with hydrofoil-equipped seaplane floats, and three had sections designed to have constant chordwise pressure distributions at given values of the lift coefficient for the purpose of delaying the speed at which cavitation begins. The experimental results are presented as curves of the lift and drag coefficients plotted against speed for the various angles of attack and depths for which the hydrofoils were tested. A number of derived curves are included for the purpose of better comparing the characteristics of the hydrofoils and to show the effects of depth. Several representative photographs show the development of cavitation on the the upper surface of the hydrofoils. The results indicate that properly designed hydrofoil sections will have excellent characteristics and that the speed at which cavitation occurs may be delayed to an appreciable extent by the use of suitable sections.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-SR-158
    Format: application/pdf
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  • 3
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    The Effects of Aerodynamic Heating on Ice Formations on Airplane Propellers (1940)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation has been made of the effect of aerodynamic heating on propeller-blade temperatures. The blade temperature rise resulting from aerodynamic heating was measured and the relation between the resulting blade temperatures and the outer limit of the iced-over region was examined. It was found that the outermost station at which ice formed on a propeller blade was determined by the blade temperature rise resulting from the aerodynamic heating at that point.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-153
    Format: application/pdf
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  • 4
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    High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane (1940)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Force tests were made of a 1/8-scale model of a twin-engine low-wing transport airplane in the NACA 8-foot high-speed wind tunnel to investigate compressibility and interference effects at speeds up to 450 miles per hour. In addition to tests of the standard arrangement of the model tests were made with several modifications designed to reduce the drag and to increase the critical speed. The results show serious increases in drag at critical speeds below 450 miles per hour due to the occurrence of compressibility burbles on the standard radial-engine cowlings, on sections of the wing as a result of wing-nacelle interference, and on the semi-retracted main landing wheels. The critical speed at which the shock occurred on the standard cowlings was 20 miles per hour lower in the presence of the fuselage than in the presence of the wing only. The drag of the complete model was reduced 25% at 300 miles per hour by completely retracting the landing gear, fairing the windshield irregularities, and substituting streamline nacelles (with allowance made for the proper amount of cooling-air flow) for the standard nacelle arrangement. The values of the critical Mach number were extended from 0.47 to 0.60 as a result of the aforementioned improvements. The principal purpose of the reported tests was to investigate the effect of compressibility on the drag of the component parts of a representative large airplane and on the overall drag of such an airplane. The influence of interference on compressibility effects was also studied. In addition, it was proposed to test several modifications of the standard component parts that gave promise of an improvement in aerodynamic characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-143
    Format: application/pdf
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  • 5
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    Mechanical Properties of Flush-Riveted Joints (1940)
    In:  CASI
    Details
    Publication Date: 2019-08-24
    Description: The strength of representative types of flush-riveted joints has been determined by testing 865 single-shearing, double-shearing, and tensile specimens representing 7 types of rivet and 18 types of joint. The results, presented in graphic form, show the stress at failure, type of failure, and d/t ratio. In general, 'dimpled' joints were appreciably stronger than countersunk or protruding-head joints, but their strength was greatly influenced by constructional details. The optimum d/t ratios have been determined for the several kinds of joints. Photomacrographs of each type show constructional details and, in several instances, cracks in the sheet.
    Keywords: Mechanical Engineering
    Type: NACA-SR-142
    Format: application/pdf
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  • 6
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    Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Karman-Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.
    Keywords: Aerodynamics
    Type: NACA-TM-1023
    Format: application/pdf
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  • 7
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    The Icing of Aircraft (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This technical memorandum presents a theoretical study of the processes accompanying the formation of ice on solid bodies. It discusses vapor pressure and sublimation in two air masses separated by a boundary area.
    Keywords: Air Transportation and Safety
    Type: NACA-TM-1028 , Beitraege zur Physik der Freien Atmosphaere; 18; 4; 235-241
    Format: application/pdf
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  • 8
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    Contribution to the Design of Plywood Shells (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The writer sets out to prove by calculation and experiment that by extensive utilization of the skin to carry axial load (reduction of stringer spacing) the stringer sections can be made small enough to afford a substantial saving in structural weight. This saving ranges from 5 to about 40 percent.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1031 , Luftfahrtforschung; 18; 9; 331-337
    Format: application/pdf
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  • 9
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    Compressibility and Heating Effects on Pressure Loss and Cooling of a Baffled Cylinder Barrel (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Theoretical investigations have shown that, because air is compressible, the pressure-drop requirements for cooling an air-cooled engine will be much greater at high altitudes and high speeds than at sea level and low speeds. Tests were conducted by the NACA to obtain some experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. The results reported in the present paper are regarded as preliminary to tests on single-cylinder and multi-cylinder engines. Tests were conducted over a wide range of air flows and density altitudes.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-783
    Format: application/pdf
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  • 10
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    Thermal Theory of Combustion and Explosion (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: This paper discusses the thermal theory of combustion and explosion, and conditions of ignition: transformation accompanied by heat liberation, transformation rate and temperature dependence.
    Keywords: Inorganic, Organic and Physical Chemistry
    Type: NACA-TM-1024 , Progress of Physical Science; 23; 3; 251-292
    Format: application/pdf
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