SURFACE PRESSURE MEASUREMENTS AT THE TIP OF A MODEL HELICOPTER ROTOR IN HOVER

Detailed blade-tip surface pressure distribution data for a single-bladed model helicopter rotor in hover are presented. The pressure measurements were made along the chordwise direction at six spanwise stations out-board of the 94 percent radial location on the rotor blade. Data were taken at blade collective pitch angles of 0, 6.2, and 11.4 deg. The points of inception of the primary vortex inferred from the pressure data agree with those noted by other investigators using surface flow visualization techniques. The presence of both a primary and a secondary vortex near the rotor tip at a pitch angle of 11.4 deg is observed. Normal and chordwise force coefficients obtained by integrating the pressure data are also presented.

  • Availability:
  • Corporate Authors:

    American Institute of Aeronautics and Astronautics

    1290 Avenue of the Americas
    New York, NY  United States  10019
  • Authors:
    • Shivananda, T P
    • McMahon, H M
    • Gray, R B
  • Publication Date: 1978-8

Media Info

  • Features: References;
  • Pagination: p. 460-467
  • Serial:
    • Journal of Aircraft
    • Volume: 15
    • Issue Number: 8
    • Publisher: American Institute of Aeronautics and Astronautics
    • ISSN: 0021-8669

Subject/Index Terms

Filing Info

  • Accession Number: 00189861
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Mar 14 1979 12:00AM