Computational Assessment of Laminar-Turbulent Transition for a Rotor in Forward-Flight Conditions

Forward-flight predictions of a rotor-fuselage system are made using a computational fluid dynamics approach. Solutions are generated using the NASA OVERFLOW solver with laminar-turbulent transition modeling enabled. Simulations are based on a hover tip Mach number of 0.57 at an advance ratio of 0.30 with prescribed collective and cyclic pitch angles. The configuration is based on a three-bladed Pressure Sensitive Paint rotor with a Rotor Body Interaction mod7 fuselage that was tested in the NASA Langley 14x22 subsonic tunnel. Grid generation and computational methods are described. The rotor and fuselage flowfield is analyzed and the effect of the transition model is assessed. Predicted forward flight performance is compared with measurements obtained at NASA Langley.