WING DESIGN BY NUMERICAL OPTIMIZATION

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:
  • Find a library where document is available. Order URL: http://worldcat.org/issn/00218669
• 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
  • Serial URL: https://arc.aiaa.org/journal/ja

Subject/Index Terms

• TRT Terms: Aerodynamics; Aircraft; Airfoils; Design; Design engineering; Lift drag ratio; Optimization; Wings (Aircraft)
• Old TRIS Terms: Design optimization; Swept wings; Wing design
• Subject Areas: Aviation; Design; Vehicles and Equipment;

Filing Info

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