EXPERIMENTAL AND THEORETICAL INVESTIGATION OF THE FLUTTER CHARACTERISTICS OF A MODEL HELICOPTER ROTOR BLADE IN FORWARD FLIGHT
Abstract
An experimental and analytical investigation was made of the effects of advance ratio on the flutter characteristics of a model helicopter rotor blade. Analyses were based on linearized equations of motion for the flapping, pitching, bending and twisting degrees of freedom although twisting was neglected in the subsequent calculations. Reversed flow effects were included in the evaluation of the aerodynamic forces. Experimental flutter data were obtained by testing a model helicopter rotor blade mounted on the CAL/TRECOM small Rotorcraft Test Apparatus. These data were compared with the results of calculations based on the linearized equations of motion for pitching, flapping and bending. The trends of the theoretical and experimental results were in fair agreement. Lack of good quantitative agreement is believed to be caused by the absence of an adequate unsteady aerodynamic theory.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1962
- Accession Number
- AD0275107
Entities
People
- Charles A. Gates
- Frank A. Duwaldt
Organizations
- Calspan