AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF ROTOR TIP SHAPE ON HELICOPTER BLADE-SLAP NOISE

The effect of tip-shape modification on blade-vortex interaction-induced helicopter blade-slap noise was investigated. The general rotor model system (GRMS) with a 3.148 m (10.33 ft) diameter, four-bladed fully articulated rotor was installed in the Langley V/STOL wind tunnel. The tunnel was operated in the open-throat configuration with treatment to improve the semi-anechoic characteristics of the test chamber. Based on previous investigation, four promising tips (ogee, sub-wing, 60 deg swept-tapered, and end-plate) were used along with a standard square tip as a baseline configuration. Aerodynamic and acoustical data concerning the relative applicability of the various tip configurations for blade-slap noise reduction are presented without analysis or discussion.

  • Supplemental Notes:
    • Prepared in Cooperation with Army Research and Technology Laboratories, Hampton.
  • Corporate Authors:

    Langley Research Center

    National Aeronautics and Space Administration
    Hampton, VA  USA  23665
  • Authors:
    • Hoad, D R
  • Publication Date: 1979-5

Media Info

  • Pagination: 464 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00198897
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-80066
  • Files: TRIS
  • Created Date: Oct 17 1980 12:00AM