Computed Effects of Heat Transfer on the Transonic Flow over an Aerofoil

摘要

The effects of the model surface to freestream adiabatic temperature ratio (Tw/Taa) on subsonic flows at zero pressure gradient and transonic flow over a NACA0012 aerofoil are evaluated using a computational fluid dynamic approach. The analysis, based on the thin layer Navier-Stokes equations with a Baldwin-Lomax turbulence model, indicated that surface heat transfer has significant effects on both subsonic and transonic flows confirming some of the experimental data available. The results have implications in wind-tunnel testing at nonadiabatic surface conditions.