Navier–Stokes Simulation of Transonic Blade-Vortex Interactions

Abstract

Transonic strong blade-vortex interaction is numerically analyzed by solving the unsteady 2-D Navier–Stokes equations using an iterative implicit second order scheme. The dominant processes during the interaction are the development of large transverse pressure gradients in the upper leading edge region and the development of disturbances at the root of the lower surface shock wave. As a result of this interaction, high pressure pulses are emitted from the leading edge, and acoustic waves are radiated from the lower surface in a region originally occupied by a supersonic pocket. In addition, severe load variations occur when the vortex is within one chord length of the blade.

Numerical Uncertainties in Transonic Flow Calculations for Aerofoils With Blunt Trailing Edges

“…The mixing length turbulence model, although not very complex, has provided good agreement in previous work 1,14,24,25 when compared to experiments and calculations with the ke model, and the present calculations compare favourably with RAE 2822 experiments. In previous benchmark calculations discussed below, recirculating, transonic and aerofoil flows with the present Reynolds-averaged Navier-Stokes solution procedure were obtained, suggesting that this code calculates the lift-to-drag ratio within less than 1% for supercritical aerofoils, although absolute values of lift and drag are bounded by about 117% and 211% uncertainty respectively.…”