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  • Other Sources  (7)
  • 2015-2019
  • 1975-1979
  • 1935-1939  (7)
  • 1810-1819
  • 1937  (7)
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  • 2015-2019
  • 1975-1979
  • 1935-1939  (7)
  • 1810-1819
Year
  • 1
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    Detonation and Autoignition : Some Considerations on Methods of Determination (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is a critical analysis of the methods of determination of the tendency to detonation. No attempt has been made to describe in detail the different fuels and the different methods proposed.
    Type: NACA-TM-843
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of Nozzle Design on Fuel Spray and Flame Formation in a High-Speed Compression-Ignition Engine (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fuel was injected from different type of injection nozzles into the combustion chamber of the NACA combustion apparatus, operated as a compression-ignition engine. High speed motion pictures were taken of the fuel sprays and combustion. Single-orifice nozzles of 0.008, 0.020, and 0.040 inch diameter, and multiorifice nozzles having 2, 6, and 16 orifices were tested. Nozzles having impinging jets and slit orifices were also included. The photographs indicate that the rate of vapor diffusion from the spray is comparatively slow and that this slow rate of diffusion for combustion chambers with little or no air flow prevents the compression-ignition engine from giving the high performance inherent in the high compression ratios. The sprays from the multiorifice nozzles destroyed the air movement to a greater extent than did those from single orifice nozzles. It is concluded that high performance cannot be realized until the methods of distributing the fuel are improved by means of the injection-nozzle design, air flow, or both.
    Type: NACA-TR-561
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Bending Tests of Circular Cylinders of Corrugated Aluminum-alloy Sheet (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Bending tests were made of two circular cylinders of corrugated aluminum-alloy sheet. In each test failure occurred by bending of the corrugations in a plane normal to the skin. It was found, after analysis of the effect of short end bays, that the computed stress on the extreme fiber of a corrugated cylinder is in excess of that for a flat panel of the same basic pattern and panel length tested as a pin-ended column. It is concluded that this increased strength was due to the effects of curvature of the pitch line. It is also concluded from the tests that light bulkheads closely spaced strengthen corrugated cylinders very materially.
    Type: NACA-TN-595
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Full-scale Wind-tunnel and Flight Tests of a Fairchild 22 Airplane Equipped with External-airfoil Flaps (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel and flight tests have been made of a Fairchild 22 airplane equipped with a wing having external-airfoil flaps that also perform the function of ailerons. Lift, drag, and pitching-moment coefficients of the airplane with several flap settings, and the rolling- and yawing-moment coefficients with the flaps deflected as ailerons were measured in the full-scale tunnel with the horizontal tail surfaces and propeller removed. The effect of the flaps on the low speed and on the take-off and landing characteristics, the effectiveness of flaps when used as ailerons, and the forces required to operate them as ailerons were determined in flight. The wind-tunnel tests showed that the flaps increased the maximum lift coefficient of the airplane from 1.51 with the flap in the minimum drag position to 2.12 with the flap in the minimum drag position to 2.12 with the flap deflected 30 degrees. In the flight tests the minimum speed decreased from 46.8 miles per hour with the flaps up to 41.3 miles per hour with the flaps deflected. The required take-off run to attain a height of 50 feet was reduced from 820 to 750 feet and the landing run from a height of 50 feet was reduced from 930 to 480 feet. The flaps for this installation gave lateral control that was not entirely satisfactory. Their rolling action was good but the adverse yaw resulting from their use was greater than is considerable, and the stick forces required to operate them increased too rapidly with speed.
    Type: NACA-TN-604
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Fuel Spray and Flame Formation in a Compression-Ignition Engine Employing Air Flow (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of air flow on fuel spray and flame formation in a high-speed compression-ignition engine have been investigated by means of the NACA combustion apparatus. The process was studied by examining high-speed motion pictures taken at the rate of 2,200 frames a second. The combustion chamber was of the flat-disk type used in previous experiments with this apparatus. The air flow was produced by a rectangular displacer mounted on top of the engine piston. Three fuel-injection nozzles were tested: a 0.020-inch single-orifice nozzle, a 6-orifice nozzle, and a slit nozzle. The air velocity within the combustion chamber was estimated to reach a value of 425 feet a second. The results show that in no case was the form of the fuel spray completely destroyed by the air jet although in some cases the direction of the spray was changed and the spray envelope was carried away by the moving air. The distribution of the fuel in the combustion chamber of a compression-ignition engine can be regulated to some extent by the design of the combustion chamber, by the design of the fuel-injection nozzle, and by the use of air flow.
    Type: NACA-TR-588
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of Air-Fuel Spray and Flame Formation in a Compression-Ignition Engine (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High-speed motion pictures were taken at the rate of 2,500 frames per second of the fuel spray and flame formation in the combustion chamber of the NACA combustion apparatus. The compression ratio was 13.2 and the speed 1,500 revolutions per minute. An optical indicator was used to record the time-pressure relationship in the combustion chamber. The air-fuel ratio was varied from 10.4 to 365. The results showed that as the air-fuel ratio was increased definite stratification of the charge occurred in the combustion chamber even though moderate air flow existed. The results also showed the rate of vapor diffusion to be relatively slow.
    Type: NACA-TR-545
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Ultrasonic measurement of core material temperature Final report (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Ultrasonic measurement of core material temperature in nuclear rocket engines
    Keywords: NUCLEAR ENGINEERING
    Type: NASA-CR-72717
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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