A study was conducted to assess the feasibility of performing computerized wing design by numerical optimization. The design program combined a full-potential, inviscid aerodynamic code with a conjugate gradient optimization algorithm. Three design problems were selected to demonstrate the design technique. The first involved modifying the upper surface of the inboard 50% of a swept wing to reduce the shock drag subject to a constraint on wing volume. The second involved modifying the entire upper surface of the same swept wing (except the tip section) to increase the lift-drag ratio, subject to constraints on wing volume and lift coefficient. The final problem involved modifying the inboard 50% of a low-speed wing to achieve good stall progression. Results from the three cases indicate that the technique is sufficiently accurate to permit substantial improvement in the design objectives.

  • Availability:
  • Corporate Authors:

    American Institute of Aeronautics and Astronautics

    1290 Avenue of the Americas
    New York, NY  United States  10019
  • Authors:
    • Hicks, R M
    • Henne, P A
  • Publication Date: 1978-7

Media Info

  • Pagination: p. 407-412
  • Serial:
    • Journal of Aircraft
    • Volume: 15
    • Issue Number: 7
    • Publisher: American Institute of Aeronautics and Astronautics
    • ISSN: 0021-8669

Subject/Index Terms

Filing Info

  • Accession Number: 00188570
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Mar 14 1979 12:00AM