The article aims to determine the effect of reverse flow on the damping, frequency, and the stability boundaries of helicopter rotor-blade flapping dynamics and to investigate the behavior of the system in the limit of small Lock number and small advance ratio. The system is represented by a linear ordinary differential equation that gives results resembling to experimental data.

Document Type

Final Report

Author's School

McKelvey School of Engineering

Author's Department

Mechanical Engineering and Materials Science

Class Name

Mechanical Engineering and Material Sciences Independent Study

Date of Submission