A three-dimensional unsteady, viscous aerodynamic analysis has been de
veloped for the flow inside a transonic, high-through-flow, single-sta
ge compressor. The compressor stage is comprised of a low-aspect ratio
rotor and a closely coupled stator. The analysis is based on a numeri
cal method for solving the three-dimensional Navier-Stokes equation fo
r unsteady viscous flow through multiple turbomachinery blade rows. Th
e method solves the fully three-dimensional Navier-Stokes equation wit
h an implicit scheme. A two-equation turbulence model with a low Reyno
lds number modification is applied for the turbulence closure. A third
-order accurate upwinding scheme is used to approximate convection ter
ms, whereas a second-order-accurate central difference scheme is used
for the discretization of the viscous terms. A second-order accurate s
cheme is employed for the temporal discretization. The numerical metho
d is applied to study the unsteady flowfield inside a transonic, high-
through-flow, axial compressor stage. The numerical results are compar
ed with available experimental data.