Article thumbnail

Wind-tunnel tests of wide-chord teetering rotors with and without outboard flapping hinges

By B. L. Lee and W. H. Weller

Abstract

Wind tunnel tests of aeroelastically designed helicopter rotor models were conducted to obtain rotor aerodynamic performance and dynamic response data pertaining to two-bladed teetering rotors with a wider chord and lower hover tip speed than currently employed on production helicopters. The effects of a flapping hinge at 62 percent radius were also studied. Finally, the effects of changing tip mass on operating characteristics of the rotor with the outboard flapping hinge were examined. The models were tested at several shaft angles of attack for five advance ratios, 0.15, 0.25, 0.35, 0.40, and 0.45. For each combination of shaft angle and advance ratio, the rotor lift was varied over a wide range to include simulated maneuver conditions. At each test condition, rotor aerodynamic performance and dynamic response data were obtained. From these tests, it was found that wide-chord rotors may be subject to large control forces. An outboard flapping hinge may be used to reduce beamwise bending moments over a significant part of the blade radius without significantly affecting the chordwise bending moments

Topics: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Year: 1977
OAI identifier: oai:casi.ntrs.nasa.gov:19780003110

Suggested articles


To submit an update or takedown request for this paper, please submit an Update/Correction/Removal Request.