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  • Aircraft Propulsion and Power  (182)
  • 1955-1959  (40)
  • 1945-1949  (126)
  • 1940-1944  (16)
  • 11
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    Performance Charts for a Turbojet System (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Convenient charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet system. These charts take into account the effects of ram pressure, compressor pressure ratio, ratio of combustion-chamber-outlet temperature to atmospheric temperature, compressor efficiency, turbine efficiency, combustion efficiency, discharge-nozzle coefficient, losses in total pressure in the inlet to the jet-propulsion unit and in the combustion chamber, and variation in specific heats with temperature. The principal performance charts show clearly the effects of the primary variables and correction charts provide the effects of the secondary variables. The performance of illustrative cases of turbojet systems is given. It is shown that maximum thrust per unit mass rate of air flow occurs at a lower compressor pressure ratio than minimum specific fuel consumption. The thrust per unit mass rate of air flow increases as the combustion-chamber discharge temperature increases. For minimum specific fuel consumption, however, an optimum combustion-chamber discharge temperature exists, which in some cases may be less than the limiting temperature imposed by the strength temperature characteristics of present materials.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-241 , NACA-ARR-E6E14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that this 25-percent increase in power will permit an approximate usable increase of 8.5 percent in the take-off load of existing military airplanes. This increase in load is equivalent to an increase in the weight of gasoline normally carried of between 30 and 65 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-117 , NACA-RB-4A25
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant properties based on the coolant bulk temperature gave the best agreement with experimental data. The agreement obtained was within 3 percent at the midspan and tip regions of the blade. At the root region of the blade, the agreement was within 3 percent for coolant flows within the turbulent flow regime and within 10 percent for coolant flows in the laminar regime. The calculated and measured cooling-air pressure losses through the blade agreed within 5 percent. Calculated spanwise blade temperatures for assumed turboprop engine operating conditions of 2000 F turbine-inlet gas temperature and flight conditions of 300 knots at a 30,000-foot altitude agreed well with those obtained by the extrapolation of correlated experimental data of a static cascade investigation of these blades.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E58E20
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Aircraft-Fuel-Tank Design for Liquid Hydrogen (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E55F22
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Adaptation of Combustion Principles to Aircraft Propulsion (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E54I07
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine I : Cooling Characteristics (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differed slightly in that the barrel of the single-cylinder engine runs cooler than the barrel of te flight engine for the same head temperatures and engine conditions.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-271 , NACA-MR-E5J04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Variation with Mach Number of Static and Total Pressures Through Various Screens (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire dimmeter for an installation so that the choking Mach number is
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Wind-tunnel Tests of Four Curtiss Propellers Embodying Different Blade Sections (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of four 10-foot propellers were made in the propeller-research tunnel for the Army Air Corps to check flight and static thrust test results made on several propellers embodying Clark Y and modified NACA 16-series sections. These propellers were identical as to diameter and activity factor and very closely identical in thickness ratio and pitch distribution. The blades embodied sections with both single- and double-cambered Clark Y, modified NACA 16-series, and a combination of Clark Y and modified NACA-16 airfoils. Tests covered a range of blade angles from 20 deg. to 70 deg., and were all made at tip speeds below 280 feet per second. Although these tests were not conclusive in themselves, owing to the conditions under which they were made, the results seem to check the flight and static tests as closely as would be expected.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-569
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination I : Performance of a Highly Supercharged Compression-Ignition Engine (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm. Exhaust pressures and temperatures were determined from an analysis of indicator cards. The analysis showed that, at rich mixtures with the exhaust back pressure equal to the inlet-air pressure, there is excess energy available for driving a turbine over that required for supercharging. The presence of this excess energy indicates that a highly supercharged compression-ignition engine might be desirable as a compressor and combustion chamber for a turbine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-234 , NACA-ARR-E5K06
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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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
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