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  • Other Sources  (69)
  • 1935-1939  (69)
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  • 1
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    Unknown
    Full-Scale Tests of a New Type NACA Nose-Slot Cowling (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An extended experimental study has been made in regard to the various refinements in the design of engine cowlings as related to the propeller-nacelle unit as a whole, under conditions corresponding to take-off, climb, and normal flight. The tests were all conducted at full scale in the 20-foot wind tunnel. This report presents the results of a novel type of engine cowling, characterized by the fact that the exit opening discharging the cooling air is not, as usual, located behind the engine but at the foremost extremity or nose of the cowling. The efficiency is found to be high, owing to the fact that higher velocities may be used in the exit opening.
    Type: NACA-TR-595
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Resistance of Transparent Plastics to Impact (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The problem of developing a windshield for aircraft which will withstand the effect of bird impacts during flight is a difficult one, as an estimate of the striking energy will indicate. If the average speed of the airplane is considered to be about 200 miles per hour and that of the bird about 70 miles per hour, the speed of the bird relative to the airplane may be as great as 400 feet per second. If a 4-pound bird is involved, a maximum impact energy of approximately 10,000 foot-pounds must be dissipated. To obtain this energy in a drop test in the Washington Monument, it would be necessary to drop a 20-pound weight down the 500-foot shaft. For both theoretical and practical reasons, it is necessary to keep the mass and speed more nearly like those to be encountered. However, to get an impact of about 10,000 foot-pounds with a 4-pound falling body, it would be necessary to drop it from a height of approximately one-half mile, neglecting air resistance. These facts will indicate some of the experimental obstacles in the way of simulating bird impacts against aircraft windshields.
    Type: NACA-TN-718
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    The cetene scale and the induction period preceding the spontaneous ignition of diesel fuels in bombs (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present report a comparison is made between the scale obtained with mixtures of cetane and l-methyl naphthalene in a bomb, and that obtained with the same fuels in a Waukesha engine. The tests were conducted in a metal bomb heated by a Nichrome spiral. The fuel was injected into the bomb from a Bosch jet by means of a specially constructed plunger pump. The instant injection and the pressure curve in the bomb were registered by a beam of light which was reflected from a mirror connected to the needle of the jet and to a membrane indicator.
    Type: NACA-TM-813
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A Study of Transparent Plastics for use on Aircraft. Supplement (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This supplement to a NACA study issued in May 1937 entitled "A Study of Transparent Plastics for Use on Aircraft", contains two tables. These tables contain data on bursting strengths of plastics, particularly at low temperatures. Table 1 contains the values reported in a table of the original memorandum, and additional values obtained at approximately 25 C, for three samples of Acrylate resin. The second table contains data obtained for the bursting strength when one surface of the plastic was cooled to approximately -35 C.
    Keywords: Nonmetallic Materials
    Type: NACA-SR-66A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Intercooler Design for Aircraft, Special Report (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: When an airplane is operating at high altitude, it is necessary to use a supercharger to maintain ground pressure at the carburetor inlet. This maintenance and high intake-manifold pressure tends to keep the power output of the engine at ground-level value. The air, being compressed by the supercharger, however, is heated by adiabatic compression and friction to a temperature that seriously affect the performance of the engine. It is thus necessary to use an intercooler to reduce the temperature of the air between the supercharger outlet and the carburetor inlet. The amount of cooling required of the intercooler depend on the efficiency of the supercharger installation. In this investigation, several types of intercoolers were compared and a design procedure that will give the best intercooler for a given set of conditions is indicated. The figure of merit used for the selection of the best design was the total power consumed by the intercooler. This value includes the power required to transport the weight of the intercooler as well as the power used to force the charge air and the cooling air through the intercooler. The cost, size and practicality of construction were not considered, inasmuch as it was thought that a survey of possibilities of improvement in design would be of interest, regardless of whether the improvement could be immediately realized. Three types of intercoolers are included in this survey: a counterflow intercooler with indirect cooling surface in the form of fins, a counterflow intercooler with direct cooling surfaces, and a cross-flow, tube-type intercooler.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-124
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A Study of Transparent Plastics for use on Aircraft, Special Report (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Various transparent organic plastics, including both commercially available and experimental materials, have been examined to determine their suitability for use as flexible windshields on aircraft, The properties which have been studied include light transmission, haziness, distortion, resistance to weathering, scratch and indentation hardness, impact strength, dimensional stability, resistance to water and various cleaning fluids, bursting strength at normal and low temperatures, and flammability.
    Keywords: Nonmetallic Materials
    Type: NACA-SR-64A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Some considerations on the fields of stresses connected with dislocations in a regular crystal lattice (1939)
    In:  Proc. Koninkl. Ned. Akad. Wetenschap., Hannover, FU Berlin, vol. 42, no. 3, pp. 293, pp. 5091692, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1939
    Keywords: Stress ; Dislocation ; Rock mechanics ; Elasticity
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    An Instrument for Estimating Tautness of Doped Fabrics on Aircraft (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-729
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental apparatus for the study of propellers (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The apparatus consists of a universal balance with transmission at variable speeds from 300 to 5,000 rpm and a group directly coupled to the model for speeds of 5 to 30,000 revolutions. This new apparatus was also designed with a torsion meter for measuring the torque. Tests were conducted on the effect of the angle between the propeller axis and the wind direction. The results presented correspond to a first series of tests made without an interposed wing and in which the distance between the plane of the propeller disk and the tail was maintained constant.
    Type: NACA-TM-819
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Cooling on the Front of an Air-cooled Engine Cylinder in a Conventional Engine Cowling (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements were made of the cooling on the fronts of model cylinders in a conventional cowling for cooling in both the ground and the cruising conditions. The mechanisms of front and rear cooling are essentially different. Cooling on the rear baffled part of the cylinders continually increases with increasing fin width. For the front of the cylinder, an optimum fin width was found to exist beyond which an increase in width reduced the heat transfer. The heat transfer coefficient on the front of the cylinders was larger on the side of the cylinder facing the propeller swirl than on the opposite side. This effect became more pronounced as the fin width was increased. These results are introductory to the study of front cooling and show the general effect of several test parameters.
    Type: NACA-TR-674
    Format: application/pdf
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