Fuselage surface pressure measurements of a helicopter wind-tunnel model with a 3.15-meter diameter single rotor

Abstract

A wind-tunnel investigation was conducted to measure the time averaged fuselage surface pressures of a helicopter model with a 3.15 meter diameter, four-bladed articulated rotor. Measurements were made at hover and advance ratios of 0.05, 0.15, and 0.20 for a range of thrusts. Data are presented with no analysis.