Numerical Simulation of Plasma Control of Separated Flows over Airfoils

Plasma actuator was modeled as body force vectors resulting from external electric field and net charge distribution in plasma. Using FLUENT User Defined Function(UDF), the body force was introduced to Navier-Stokes equations as source term to simulate the flat jet induced by plasma actuator, as well as the dielectric barrier discharge (DBD) plasma excitation of NACA0015 airfoil at large attack angle separation flow control. The simulation show that the multi electrode plasma actuator can control the flow separation of NACA0015 airfoil at high angle of attack effectively.