HELICOPTER BLADE SLAP,
Abstract
The paper considers a possible mechanism for the generation of blade slap. A simplified theory for this is presented which shows good agreement with the results obtained from a test rig on which blade slap was simulated. In particular it show that the noise is dependent on the fourth power of the velocity and the square of the gust size (vortex strength). The results are sufficiently encouraging to warrant the extension of the analysis to that of an actual helicopter. Normally, blade element velocity in a helicopter can not be varied appreciably; it is fixed by far more important aerodynamic considerations. The profile of a vortex and its path are very important considerations that may possibly be partially controllable. Because the noise increases with the square of the vortex velocity amplitude (W), highly loaded rotor blades, which produce a strong tip vortex have a greater penchant toward loud blade slap. This contributes to the severity of the blade slap on the IROQUOIS which has a highly loaded two-bladed rotor. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1966
- Accession Number
- AD0634644
Entities
People
- F. Webb Taylor
- John W. Leverton
Organizations
- University of Southampton