ROTATING CYLINDER FOR CIRCULATION CONTROL ON AN AIRFOIL

The lift augmentation effect of a rotating cylinder located at the truncated trailing edge of a body is presented. A symmetrical airfoil model with a trailing-edge cylinder was tested in a low-speed wind tunnel, and the lift produced as a function of cylinder speed was determined for cylinder speeds up to three times the freestream velocity. Since the lift was attained at a 0ous geometric angle of attack, the lift- producing phenomenon is called circulation control, which results from the alteration of the wake region by the spinning cylinder. The lift coefficients was found to be a linear function of the ratio of cylinder speed to freestream velocity and reached a value of 1.20 at a speed ratio of 3.0. A comparison is made with a lone spinning cylinder in a crossflow (magnus effect) and the cylinder-forebody combination reported herein. The cylinder-forebody pair produces higher values of lift at a given cylinder speed and a linear response in contrast to the nonlinear response of the lone cylinder at low cylinder speeds.

  • Supplemental Notes:
    • Work was sponsored by the U.S. Navy Ship Research and Development Center, Contract No. N00014-71-A-0121-006.
  • Corporate Authors:

    American Institute of Aeronautics and Astronautics

    1290 Avenue of the Americas
    New York, NY  USA  10019
  • Authors:
    • Tennant, J S
    • Johnson, W S
    • Krothapalli, A
  • Publication Date: 1976-7

Media Info

  • Features: References;
  • Pagination: p. 102-105
  • Serial:

Subject/Index Terms

Filing Info

  • Accession Number: 00141475
  • Record Type: Publication
  • Source Agency: American Institute of Aeronautics and Astronautics
  • Files: TRIS
  • Created Date: Nov 3 1976 12:00AM