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  United States  10019
• Authors:
  • Tennant, J S
  • Johnson, W S
  • Krothapalli, A
• Publication Date: 1976-7

Media Info

• Features: References;
• Pagination: p. 102-105
• Serial:
  • Journal of Hydronautics
  • Volume: 10
  • Issue Number: 3
  • Publisher: American Institute of Aeronautics and Astronautics

Subject/Index Terms

• TRT Terms: Aerodynamic lift; Cylindrical bodies; Thrust; Wakes
• Old TRIS Terms: Lift augmentation; Wake analysis
• Subject Areas: Design; Marine Transportation;

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