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  • Other Sources  (5)
  • Aircraft Propulsion and Power  (5)
  • 2000-2004
  • 1950-1954
  • 1940-1944  (5)
  • 1935-1939
  • 1943  (3)
  • 1940  (2)
Collection
  • Other Sources  (5)
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  • 2000-2004
  • 1950-1954
  • 1940-1944  (5)
  • 1935-1939
Year
  • 1
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    Operating Temperatures of a Sodium-Cooled Exhaust Valve as Measured by a Thermocouple (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A thermocouple was installed in the crown of a sodium-cooled exhaust valve. The valve was then tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 F was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 rpm. Fuel-air ratio was found to have a large influence on valve temperature, but cooling-air pressure and variation in spark advance had little effect. An increase in engine power by change of speed or mean effective pressure increased the valve temperature. It was found that the temperature of the rear spark-plug bushing was not a satisfactory indication of the temperature of the exhaust valve.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-140 , NACA-ARR-3L06
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Measurement of Fuel-Air Ratio by Analysis for the Oxidized Exhaust Gas (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs for the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-757
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1943)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made.
    Keywords: Aircraft Propulsion and Power
    Type: NACA/TR-802
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental Determination of Exhaust Gas Thrust, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This investigation presents the results of tests made on a radial engine to determine the thrust that can be obtained from the exhaust gas when discharged from separate stacks and when discharged from the collector ring with various discharge nozzles. The engine was provided with a propeller to absorb the power and was mounted on a test stand equipped with scales for measuring the thrust and engine torque. The results indicate that at full open throttle at sea level, for the engine tested, a gain in thrust horsepower of 18 percent using separate stacks, and 9.5 percent using a collector ring and discharge nozzle, can be expected at an air speed of 550 miles per hour.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-139
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Flight Tests of Exhaust Gas Jet Propulsion, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Flight test s were conducted on the XP-41 airplane, equipped with a Pratt & Whitney R1830-19, 14-cylinder, air-cooled engine, to determine the increase in flight speed obtainable by the use of individual exhaust stacks directed rearwardly to obtain exhaust-gas thrust. Speed increases up to 18 miles per hour at 20,000 feet altitude were obtained using stacks having an exit area of 3.42 square inches for each cylinder. A slight increase in engine power and decrease in cylinder temperature at a given manifold pressure were obtained with the individual stacks as compared with a collector-ring installation. Exhaust-flame visibility was quite low, particularly in the rich range of fuel-air ratios.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-165
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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