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Validation of Comprehensive Helicopter Aeroelastic Analysis with Experimental Data

Bhat, Shrinivas R and Ganguli, Ranjan (2004) Validation of Comprehensive Helicopter Aeroelastic Analysis with Experimental Data. In: Defence Science Journal, 54 (4). pp. 419-427.

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Abstract

The experimental data for a 4-bladed soft-inplane hingeless main rotor is used to validate a comprehensive aeroelastic analysis. A finite element model has been developed for the rotor blade which predicts rotating frequencies quite well, across a range of rotation speeds. The helicopter is trimmed and the predicted trim-control angles are found to be in the range of measured values for a variety of flight speeds. Power predictions over a range of forward speeds also compare well. Finally, the aeroelastic analysis is used to study the importance of aerodynamic models on the vibration prediction. Unsteady aerodynamics and free-wake models have been investigated.

Item Type: Journal Article
Additional Information: The copyright for this article belongs to Defence Scientific Information Documentation Centre.
Keywords: Helicopter;vibration;validation;aeroelastic analysis;finite element model;rotor blade;aerodynamic models;free-wake models;unsteady aerodynamics;quasi-steady
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Date Deposited: 15 Apr 2005
Last Modified: 20 Jan 2012 09:21
URI: http://eprints.iisc.ernet.in/id/eprint/3027

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