The basic problem of a flapped NACA-16 foil is its poor pressure distribution around the flapped region. With the flap deflected, the velocity distribution becomes a very unfavorable shape in terms of cavitation-inception and boundary-layer separation. This type of flowfield results in low flap effectiveness. Based on the present profile design and boundary-layer calculation methods, improved hydrofoil wings with flaps have been developed. The approaches to construct the desired velocity distributions to delay cavitation and boundary-layer separation are discussed. Examples are given for the case that the flap deflection has to compensate the vertical component of the surface wave motion in a seaway.

  • Supplemental Notes:
    • Presented as Paper 78-726 at the AIAA/SNAME Advanced Marine Vehicles Conference, San Diego, April 17-19, 1978.
  • Corporate Authors:

    American Institute of Aeronautics and Astronautics

    1290 Avenue of the Americas
    New York, NY  United States  10019
  • Authors:
    • Shen, Y T
    • Eppler, R
  • Publication Date: 1979-4

Media Info

  • Features: References;
  • Pagination: p. 39-45
  • Serial:

Subject/Index Terms

Filing Info

  • Accession Number: 00194549
  • Record Type: Publication
  • Source Agency: American Institute of Aeronautics and Astronautics
  • Files: TRIS
  • Created Date: Jun 13 1979 12:00AM