Boundary-layers integral analysis - Airfoil icing

Abstract

Various classic icing codes have been developed and used by the aircraft manufacturers to predict the ice shapes evolution in non-protected airfoil surfaces. These codes apply boundary layer integral analysis, based on sand grain roughness, to estimate the convective heat transfer coefficient around the iced airfoil and adopt abrupt transition between laminar and turbulent flow. In the present work, the integral analysis is also used but a smooth laminar-turbulent transition model, based in the intermittency concept, is included. The transition onset position is estimated by empirical correlations or just imposed. The ice accretion on a NACA 0012 airfoil is simulated with a new convective heat transfer routine, which assumes smooth laminar-turbulent transition, and the results are compared with the ice shapes generated by ONERA2D original code and with experimental data. Copyright © 2008 by Luciano M. Stefanini, Otavio M. Silvares, Guilherme A. L. Silva, Eyriale J.G.J. Zerbini.