AN ANALYTICAL STUDY FOR SUBSONIC OBLIQUE WING TRANSPORT CONCEPT

The oblique wing concept has been investigated for subsonic transport application for a cruise Mach number of 0.95. Three different mission applications were considered and the concept analyzed against the selected mission requirements. Configuration studies determined the best area of applicability to be a commercial passenger transport mission. The critical parameter for the oblique wing concept was found to be aspect ratio which was limited to a value of 6.0 due to aeroelastic divergence. Comparison of the concept final configuration was made with fixed winged configurations designed to cruise at Mach 0.85 and 0.95. The crossover Mach number for the oblique wing concept was found to be Mach 0.91 for takeoff gross weight and direct operating cost. Benefits include reduced takeoff distance, installed thrust and mission block fuel and improved community noise characteristics. The variable geometry feature enables the final configuration to increase range by 10% at Mach 0.712 and to increase endurance by as much as 44%. (Author)

  • Corporate Authors:

    Lockheed-Georgia Company

    Marietta, GA  USA 
  • Authors:
    • Bradley, E S
    • HONRATH, J
    • Tomlin, K H
    • Swift, G
    • Shumpert, P
  • Publication Date: 1976-7

Media Info

  • Pagination: 219 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00151569
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-CR-137896
  • Contract Numbers: NAS2-8686
  • Files: TRIS
  • Created Date: Apr 13 1977 12:00AM