The primary NASA application of the proposed SWBLI control simulation tool is active flow control for inlet of scramjet engine to ensure efficient combustion and increase reliability of the hypersonic vehicles. In addition, NASA scientists will get predictable plasma-based active flow separation control simulation tool for a number of NASA projects, such as Subsonic Fixed Wing Project, Subsonic Rotary Wing Project. Finally, the proposed simulation tool, coupled with existing NASA high-fidelity CFD tools, will ensure solution of multi-physics problems, such as full simulations of plasma-assisted combustion for in-flight conditions. Active flow control using DBD plasma actuators is of interest to a number of government agencies, private industry and universities. Proposed concept and associated simulation tool will be beneficial for hypersonic and subsonic programs, involving plasma-based control concepts. These programs include, but are not limited to, development of hypersonic aircrafts, such as DARPA FALCON program and Boeing X-51, active flow separation control at UAVs and commercial airplanes during take-off, landing or maneuvering, improvement of engine performance. Besides the primary application for a SWBLI control, proposed tool can be used for a wide range of plasma aerodynamics applications, such as plasma-assisted combustion, de-icing of aircraft wings and efficient operation of windmills at high angles of attack.