Numerical Simulations of the HVAB Rotor in Hover

Abstract

Numerical simulations of compressible viscous flow over the Hover Validation and Acoustic Baseline (HVAB) rotor in hover are presented. The commercial flow solver, ANSYS Fluent, has been employed. The effects of transition are modeled using the Langtry-Menter k-ω SST-γ-Reθ model at three different pitch settings. Comparisons with HVAB test data and other publications are discussed. These include integrated thrust and power coefficients, figure of merit, velocity inflow, surface pressure distribution, lift distribution, transition locations, and vortex structures.