The new trend in aviation industry is towards „all electric aircraft‟. Thus, there‟s a strong desire to replace bleed air systems with efficient electrical ice protection systems that would provide adequate ice protection. In the current thesis study, a computational methodology was developed to support the design and assess the performance of electro-thermal ice protection systems (ETIPS) for de-icing fixed wing aircraft. The methodology developed was tested using a range of geometries and electrical heater configurations and was validated with experimental data obtained by researchers at Wichita State University (WSU) and other organizations.