The transition from laminar to turbulent flow in boundary layers significantly affects aerodynamic performance, drag, and fuel efficiency in aerospace applications. This study presents a numerical investigation into the use of Dielectric Barrier Discharge plasma actuators as an active flow control method to delay transition and reduce drag. A physics-based body force model based on the Shyy formulation was implemented via User Defined Functions in ANSYS Fluent to simulate plasma actuation effects. A series of simulations were conducted on a flat plate configuration using the transition SST model to validate baseline transition behavior against NASA benchmark data. Parametric studies were then performed to assess the influence of key actuator parameters, including electric field strength and electrode positioning, on boundary layer stability and transition onset.