Researchers: Dr. L. N. Sankar and Mert Berkman
This study aims at developing a hybrid solver that makes use of
the advantages of different routines into a single solver. Navier-Stokes
equations are the only way to model the viscous effects. However,
away from the body viscosity is usually negligible where potential
equations are valid.
Significant computional time can be saved by using these equations
instead of N.-S. equations. Hybrid solvers have previously been
developed by Sankar and his co-workers for 3-D unsteady flows over
fixed and rotary wings. In this study a free wake model is
incorporated in the potential zone to model the wake structure. The wake
model is a crucial part in rotor flows since
rotor wake dominates the flow field.
The figures below compare the numerical solution to experimental data.
The rotor: two-bladed, rectangular planform, no twist, NACA 0012 section
Flow conditions: Re=2 million, Tip Mach #=0.44
Hover Case
The rotor: 4-bladed, maximum twist=13 deg, rearward sweep of 20 deg
starting at 93% radii.
Flow conditions: Re=2.5 million, Tip Mach #=0.63
Hover Case
The rotor: two-bladed, rectangular planform, no twist, NACA 0012 section
Flow conditions: Re=2 million, Tip Mach #=0.44
Hover Case
The rotor: 4-bladed, maximum twist=13 deg, rearward sweep of 20 deg starting at 93% radii.
Flow conditions: Re=2.5 million, Tip Mach #=0.63
Hover Case