## 1 Introduction  
Electric Propulsion (EP) is an alternative type of rocket propulsion with higher efficiency at long operation maneuvering when compared to conventional chemical propulsion. It has become a well-established technology in propulsion devices for small satellites, such as Cubesats [1]. The electrohydrodynamic effect (EHD) is related to the possibility of generating or altering a gas flow, also known as ionic wind, through the action of an electrical discharge, often a corona discharge. An EHD thruster, while working with partially ionized gas, is fuel-efficient, though at the expense of electrical power to sustain the plasma formation and ensuing gas acceleration. The design of an EHD thruster is challenging as its fundamental physics is complex, combining fluid mechanics, plasma physics, and chemistry. The EHD thrust relies substantially on the flow pattern resulting from the electrode geometry and the electric potential morphology best suited for optimized performance. According to [PERSON] and [PERSON] [2], plasma propulsion is potentially the most energy-efficient mechanism, about 50 times more efficient than jet engines. However, this technology requires maturity for interplanetary-manned missions based on becoming practical. This report introduces the model and accompanying study of an electrohydrodynamic thruster, which has an externally applied electric field that induces an ionic wind--the flow of an electrically charged fluid--that transfers momentum to the neutral heavy species in a gas, thus generating a flowing stream. Particle momentum is transmitted to the ions and the neutrals, but more efficiently to the later ones due to the low degree of ionization. In its principles, the EHD thruster is a non-equilibrium non-thermal, corona discharge, consisting basically of an emitter electrode (or anode) and a collector electrode (or cathode). With its very sharp endpoint, the anode promotes the gas ionization in the high-field ionization region when a high dc voltage is applied, thus producing the thrust due to the oriented migration of the charged cloud essentially in the drift region. The EHD device moves in the opposite direction of the ion swarm, obeying the action-to-reaction law. Numerical and experimental studies of EHD propulsion systems show that a thrust to power ratio of 100 mN/W can be achieved, despite an energy conversion efficiency of less than one. Other applications can be engineered, such as boundary layer enhancement, fluid pumping (including EHD micropumps), flow, heat transfer improvement, and drying and evaporation (see, e.g., Refs. [3; 4; 5]). There are several theoretical, modulation, simulation, and experimental works that study the creation of an ionic wind resulting from the electrohydrodynamic force (EHD) created by a corona discharge, some with applications in electric propulsion (see, e.g., Refs. [6; 7; 8; 9; 10; 11; 12; 13; 14]). In 1967, [PERSON] and [PERSON] [15] investigated ionic wind as a propulsion technique. A NASA technical note [16] examined how the thrust produced by the ionic wind can scale to values of interest in aeronautical propulsion--with no moving parts, virtually silent, and no fuel emission. With inconclusive results about possible advantages, the authors concluded that corona discharges are not practical in aeronautical propulsion. However, recently, [PERSON] et al. [17] claim to have provided proof of aeronautical propulsion based on electro-aerodynamics, opening doors to avionics and aerodynamic devices that are quieter, mechanically simpler, and that do not produce fuel emission. [PERSON] et al. [18] simulated the EHD flux induced by a corona discharge, using an asymmetric high voltage capacitor to study the dependence of the thrust on parameters such as altitude, pressure, temperature, and humidity. [PERSON] et al. [19] used a source of weakly ionized gases generated in helium at atmospheric pressure to study the flow paths of different discharge parameters.