Two-Dimensional Wind Tunnel Tests of an H34 Main Rotor Airfoil Section

摘要

Tests were conducted in the two-dimensional channel of an 8 foot wind tunnel at Mach numbers from 0.30 to 0.80 to determine the surface pressure distributions on a Sikorsky H-34 main rotor production blade section. Twenty-nine static pressure taps were located on the upper and lower surfaces of the model. In addition three component force and moment measurements were obtained, along with a limited amount of wake survey drag data. The pressure coefficients are tabulated for each Mach number and angle of attack. The variation of force and moment coefficient with angle of attack at each Mach number is also included.