Hajar Mali

 

Abstract

 

Numerical simulations of compressible viscous flow over the HVAB (Hover Verification and Acoustic Baseline) rotor in hover are presented. A commercial flow solver, ANSYS Fluent, has been used.  The effects of transition turbulence are modeled using a k-omega-SST model, while the effects of transition are modeled using the Langtry-Menter transitional shear stress transport turbulence model.  The rotor is assumed to be rigid. The coning and lead lag angle were numerically computed in a post-processing step by setting the moments generated by the aerodynamic forces and the centrifugal forces at the flap and lead-lag hinges to be zero.  Comparisons with other published data are presented. These include integrated thrust and power coefficients, figure of merit, surface pressure distribution, and coning angles.

 

The proposed work focuses on remodeling the rotor with refined grids to improve the accuracy of the hover performance predictions, capture the wake more accurately, and assess the effects and location of transition.