Numerical design and analysis of a multi-DBD actuator configuration for the experimental testing of ACHEON nozzle model

Two dimensional numerical simulations of plasma actuator flow control of the ACHEON nozzle are conducted to give insight on the design of an experimental setup. Three configurations of the plasma actuators with single and multi AC-DBD actuators are used in steady mode of operation. AC-DBD actuators in standard mode (forward forcing mode), reverse mode (backward forcing mode) and plasma synthetic jets mode were used. Three different main groups of test cases were investigated by varying the reference velocity at the inlet of the nozzle stream from 4, 5 and 6 m/s. Moreover, each group includes four velocity ratios V R = 1 , 1.5 , 2 , 2.5 . The locations of the flow separation points are obtained numerically for all these cases and the plasma actuators are placed slightly upstream of these points leading to a system of seven DBD plasma actuators in the forward forcing mode over the Coanda surface. The induced thrust of the AC-DBD plasma actuators was estimated using a phenomenological model which considers the maximum achieved voltage and frequency from the experiments. Using an excitation voltage with maximum amplitude of 12 kVpp and frequency of 20 kHz, ionic wind was formed with 2.4 m/s velocity. The effects of plasma actuator are presented through change of the thrust and velocity angle and thrust vectoring efficiency. Preliminary results of the experimental set-up correlate well with the numerical design values.