Transonic flow over a supercritical aerofoil with heat transfer

摘要

The effects of the model surface to freestream adiabatic temperature ratio (T_w/T_ad) on transonic flow over a super critical arerofoil are evaluated using a computational fluid dynamci approach. The analysis based on the Thin Layer Navier Stokes Equations with Baldwin Lomax Navier Stokes Euqations with Baldwin Lomax turbulence model indicated that surface heat transfer has significant effects on transonic flows confirming some of the earlier computations on a NACA0012 profile and experimental data on biconvex aerofoils. The results have implications in wind tunnel testing of aerofoils at non-adiabatic surface conditions.