NASA computer codes in the areas of preliminary sizing and enroute performance, takeoff and landing performance, aircraft noise prediction, and economics were used in a preliminary noise tradeoff study for a Mach 2.7 design supersonic cruise concept. Aerodynamic configuration data were based on wind-tunnel model tests and related analyses. Aircraft structural characteristics and weight were based on advanced structural design methodologies, assuming conventional titanium technology. The most advanced noise prediction techniques available were used, and aircraft operating costs were estimated using accepted industry methods. The 4-engines cycles included in the study were based on assumed 1985 technology levels. Propulsion data was provided by aircraft manufacturers. Additional empirical data is needed to define both noise reduction features and other operating characteristics of all engine cycles under study. Data on VCE design parameters, coannular nozzle inverted flow noise reduction and advanced mechanical suppressors are urgently needed to reduce the present uncertainties in studies of this type.

  • Corporate Authors:

    Langley Research Center

    Advanced Research and Technical Office
    Langley Station, VA  United States  23365
  • Authors:
    • Mascitti, V R
    • Maglieri, D J
    • Raney, J P
  • Publication Date: 1979-4

Media Info

  • Pagination: 50 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00197956
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-78732
  • Files: TRIS
  • Created Date: Sep 15 1980 12:00AM