Laser Velocimeter Measurements of the Helicopter Rotor‐Induced Flow Field

Abstract

The use of a two‐color laser velocimeter to measure the flow velocities in the wake of a helicopter rotor is discussed, including methods for obtaining two components of both instantaneous and time‐averaged velocities. Results are presented from an experiment using a 2.13 m (7 ft) diameter model helicopter rotor operating at a tip speed ratio of 0.18 in a wind tunnel. The location of the tip vortex from the preceding blade was determined on the advancing side, and the diameter of the vortex core was found to be 15 percent of the blade chord (1.5&% of the radius). The effects of the airfoil's bound vorticity were observed in the velocity distributions very near the blade. These effects suggest that the laser velocimeter may be used to determine the aerodynamic loading (circulation) at a spanwise station on the blade. Also, the structure and boundary of the time‐averaged wake were investigated. It is concluded that the laser velocimeter, using the techniques shown, is a practical tool for mapping the rotor flow field for use in refining and validating theoretical predictions.