Helicopter blade-vortex interaction locations : Scale-model acoustics and free-wake analysis results
- Hoad, Danny R.
- Apr 1, 1987.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- The results of a model rotor acoustic test in the Langley 4by 7-Meter Tunnel are used to evaluate a free-wake analytical technique. An acoustic triangulation technique is used to locate the position in the rotor disk where the blade-vortex interaction noise originates. These locations, along with results of the rotor free-wake analysis, are used to define the geometry of the blade-vortex interaction noise phenomena as well as to determine if the free-wake analysis is a capable diagnostic tool. Data from tests of two teetering rotor systems are used in these analyses.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19870009104.
Accession ID: 87N18537.
- No Copyright.
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