The present invention relates to a method of controlling an aircraft,
missile, munition or ground vehicle with plasma actuators, and more
particularly to controlling fluid flow across their surfaces or other
surfaces, which would benefit from such a method. The method includes the
design of an aerodynamic plasma actuator for the purpose of controlling
airflow separation over a control surface of a aircraft, missile, or a
ground vehicle, and more particularly to the method of determining a
modulation frequency for the plasma actuator for the purpose of fluid
flow control over these vehicles. The various embodiments provide the
steps to increase the efficiency of aircraft, missiles, munitions and
ground vehicles. The method of flow control provides a means for reducing
aircraft, missile's, munition's and ground vehicle's power requirements.
These methods also provide alternate means for aerodynamic control using
low-power hingeless plasma actuator devices.