Experimental Investigation of Three Rotor Hub Fairing Shapes
DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
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A series of subsonic wind tunnel evaluations were undertaken to establish minimum drag fairings for helicopter hubs as part of the Helicopter drag Technology Program. The data reported were taken to investigate the flow phenomena affecting helicopter rotor hubs. Three large, 25 percent thick, analytically faired hubs were evaluated both with and without simulated rotor blade shanks over a wide range of angles of attack at full scale Reynolds numbers. Forces, moments, and pressures were measured on the hubs.