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  • PROPULSION SYSTEMS  (323)
  • 1970-1974  (323)
  • 1960-1964
  • 1971  (323)
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  • 1970-1974  (323)
  • 1960-1964
Year
  • 1
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    Design of Liquid Propellant Rocket Engines Second Edition (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Liquid propellant rocket engine conference proceedings and parameters for design of rocket engines and systems
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-125
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Solid Rocket Motor Performance Analysis and Prediction (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Current design practices are reviewed and assessed, and guidance is established for achieving greater consistency in design, reliability in the end product, and efficiency in the design effort. The total problem is discussed, and design elements involved in successful design are identified. Design criteria are described, and the rule, guide, limitation, or standard which must be imposed on each essential design element is given. Recommended practices are presented for satisfying each of the criteria.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-8039
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced injector concepts investigation Final summary report (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Evaluation of throttling injector concepts applicable to advanced cryogenic engines
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-103183 , REPT-21052-3FS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Installation and integration of transonic transport propulsion systems. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Initial work indicates that a viable aircraft family can be designed for higher subsonic cruise speeds. Studies to date suggest that the propulsion system/nacelle design and the incorporation of noise attenuation into this design will have more influence on the choice of an optimum engine than engine weight and fuel consumption. These studies also suggest the payoff resulting from the incorporation of new technology items such as the internal engine generator and new structural cowl concepts because of the greater sensitivity to drag. These factors, plus the greater interdependency of the transonic aircraft and its propulsion system, point up the importance of a total system approach to propulsion system optimization and design.
    Keywords: PROPULSION SYSTEMS
    Type: SAE PAPER 710762 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of a 10 mlb biowaste resistojet. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Description of the thrusting performance of a 10-mlb thrust, concentric-tubes biowaste resistojet, which was life tested on hydrogen and ammonia propellants for 8000 hours. Thrusting performance is presented for H2, H2O, CH4, and CO2 as well as typical biopropellant mixtures CO2-CH4, H2O-CH4 and CO2-H2O. Using Pt-Ir alloy heater tubes, 235 and 575 seconds were obtained for water and hydrogen propellants. Overall total power efficiencies were 66%, which includes losses for a preevaporator close-coupled for the water tests. Vibration to 1.0 sq q/Hz with an overall G rms of 36, shock at 30 g's and acceleration to 8 g's simulating a launch were passed by the thrustor.
    Keywords: PROPULSION SYSTEMS
    Type: SAE PAPER 710769 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    The NASA Quiet Engine. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The NASA Quiet Engine Program will incorporate all available noise-reduction technology into a propulsion system suitable for subsonic civil transport aircraft. Full-scale experimental hardware is being built and tested primarily for noise performance. The program is in process, and component tests to date indicate that it is possible to achieve or exceed noise reduction objectives of 15-20 PNdB below the levels of 707/DC-8 long-range transport aircraft.
    Keywords: PROPULSION SYSTEMS
    Type: SAE PAPER 710774 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Development of the Algol III solid rocket motor for SCOUT. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The design and performance of a motor developed for the first stage of the NASA SCOUT-D and E launch vehicles are discussed. The motor delivers a 30% higher total impulse and a 35 to 45% higher payload mass capability than its predecessor, the Algol IIB. The motor is 45 in. in diameter, has a length-to-diameter ratio of 8:1 and delivers an average 100,000-lb thrust for an action time of 72 sec. The motor design features a very high volumetrically loaded internal-burning charge of 17% aluminized polybutadiene propellant, a plasma-welded and heat-treated steel alloy case, and an all-ablative plastic nose liner enclosed in a steel shell. The only significant development problem was the grain design tailoring to account for erosive burning effects which occurred in the high-subsonic-Mach-number port. The tests performed on the motor are described.
    Keywords: PROPULSION SYSTEMS
    Type: SAE PAPER 710765 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Methods for reducing pollutant emissions from jet aircraft. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The purpose of this paper is to define the problem of pollutant emissions from jet aircraft and to review NASA-Lewis combustion research aimed at reducing these emissions. The problem of smoke formation and results achieved in smoke reduction from commercial combustors are discussed. Experimental results of parametric tests performed on both conventional and experimental combustors over a range of combustor-inlet conditions are presented. Combustor design techniques for reducing pollutant emissions are discussed. Improved fuel atomization resulting from the use of air-assist fuel nozzles has brought about significant reductions in hydrocarbon and carbon monoxide emissions at idle. Diffuser tests have shown that the combustor-inlet airflow profile can be controlled through the use of diffuser-wall bleed and that it may thus be possible to reduce emissions by controlling combustor airflow distribution. Emissions of nitric oxide from a shortlength annular swirl-can combustor were significantly lower than those from a conventional combustor operating at similar conditions.
    Keywords: PROPULSION SYSTEMS
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Hypersonic research engine project. Phase 2: Structures and cooling development (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Testing of the structures assembly model (SAM) continued at the Langley 8-foot high-temperature structures tunnel. A total of 30 test runs were completed, involving 38 loading cycles for the SAM. Fuel injection was used during 27 of the cycles. That portion of the program specifically aimed at thermal-cycling evaluation was completed. For these runs, tunnel total conditions ranged to 2200 psia and 3000 R. The tunnel nozzle is fixed and produces Mach numbers near 7 at the test conditions. The coolant for all runs was ambient-temperature hydrogen. The condition of the SAM following these runs was satisfactory. Isolated leaks occurred at joints in the cooled structure, but they have not affected operation or resulted in local areas of overheating. Three punctures in the leading edge, caused by foreign object damage, were present during most of the run; however, they showed no signs of propagation or distress due to overheating.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-112057 , AP-71-7185
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The analytical effort was directed toward (1) analyzing the latest inputs of possible test conditions and their impact on hardware; (2) review structural capabilities of the AIM unit; (3) analyzing coolant flow paths, heat transfer, and associated problems relative to the cowl leading edge tip section; and (4) redefining requirements of flow-calibrating the air-metering duct.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-112059 , AP-70-7035 , ITDR-11
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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