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  • 1990-1994  (4)
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  • 1
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    Unknown
    A NASA Lewis comparative propulsion system assessment for the High-Speed Civil Transport (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The topics covered include the following: High Speed Research (HSR) Propulsion System Studies; HRS System Study flowpath; design point aircraft sizing - no noise constraint; impact of noise constraint; noise impact on aircraft size; takeoff gross weight assessment; impact of High Speed Civil Transport (HSCT) high-altitude flyover noise; HSR NO(x) reduction status; current assessment of HSCT ozone depletion; influence of non-optimum cruise altitude on range; and influence of subsonic leg on range.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, First Annual High-Speed Research Workshop, Part 2; p 831-865
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    An interactive preprocessor for the NASA engine performance program (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Simplified NEPP Automated Preprocessor (SNAP), which is written to aid in the preparation of input data files for the NASA Engine Performance Program (NEPP), is described. Specifically, SNAP is a software package on the Virtual Machine operating system that prompts the NEPP user for input information via a series of menus. The data collected from these menus are assimilated into an input file suitable for the running of NEPP. SNAP acts as a user-friendly preprocessing interface for NEPP. This serves as an introduction to the SNAP software, a user's manual, a description of the program logic, and a maintenance manual for future modifications to the software.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-105786 , E-7216 , NAS 1.15:105786
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Divergence thrust loss calculations for convergent-divergent nozzles: Extensions to the classical case (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The analytical derivations of the non-axial thrust divergence losses for convergent-divergent nozzles are described as well as how these calculations are embodied in the Navy/NASA engine computer program. The convergent-divergent geometries considered are simple classic axisymmetric nozzles, two dimensional rectangular nozzles, and axisymmetric and two dimensional plug nozzles. A simple, traditional, inviscid mathematical approach is used to deduce the influence of the ineffectual non-axial thrust as a function of the nozzle exit divergence angle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-105176 , E-6472 , NAS 1.15:105176
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of turbine bypass and mixed flow turbofan engines for a high-speed civil transport (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A comparison of the turbine bypass engine and the mixed flow turbofan for a Mach 2.4 cruise application is presented. A parametric assessment is conducted for each cycle. Parameters that are investigated for the turbine bypass engine include design bypass, combustor exit temperature, and overall pressure ratio. Parameters that are investigated for the mixed flow turbofan include fan pressure ratio, mixer design pressure ratio, and combustor exit temperature. The engines are analyzed for a 5000-nautical-mile, all supersonic cruise mission to determine the aircraft takeoff gross weights. The effects of takeoff noise, cruise emissions, the addition of subsonic cruise legs, and constrained supersonic cruise altitudes are also evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-3132
    Format: text
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    NASA TECHNICAL REPORTS
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