Computational Investigation of a Bleed Air Ice Protection System

A computational study was conducted to investigate the performance of a hot air antiicing system under dry external flow conditions. The hot air system consisted of a piccolo tube and an inner-liner skin installed inside the leading edge of a 72-in span, 60-in chord business jet wing model. A conjugate heat transfer analysis was performed with a threedimensional Navier-Stokes computer code to compute leading edge skin temperatures and hot air system internal flow properties. Simulations were conducted with a full-span model (FSM) to investigate the flow development inside the piccolo tube and with a partial-span model (PSM) to compute hot air system performance. The computational results obtained were compared with experimental data obtained from icing tunnel tests at the NASA Glenn Icing Research Tunnel. Computed leading edge skin temperatures, piccolo centerline total temperatures and pressures were found to be in good agreement with the experimental data.