PECyT - Plasma Enhanced Cycloidal Thruster

Abstract

In the following paper we introduce PECyT system for enhancing the aerodynamic efficiency of cycloidal rotors. For that purpose the incorporation of Dielectric Barrier Discharge plasma actuators for active flow control on a pitching airfoil, under deep-stall conditions, will be assessed using a numerical tool. Two different arrangements of DBD actuators will be analysed, namely single- and multi-DBDs configurations. For the single- DBD plasma actuator the effect of different modes of actuation on the lift coefficient will also be studied. We will show that the multi-DBD actuator, in a steady-actuation mode, could delay stall and allows for a faster reattachment of the flow. However during the downstroke phase of the pitching cycle the unsteady operation of a single-DBD gives us the best results in terms of lift coefficient

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

“…Previous results have shown that the influence of the DBDs on each other is additive and our CFD results [33] have shown that, the Multi-DBD system will causes ionic wind with higher intensity. To confirm this and to better understand how a multi-DBD actuator is more effective than a single DBD actuator, Fig.…”

Numerical Analysis of Design Parameters With Strong Influence on the Aerodynamic Efficiency of a Small-Scale Self-Pitch VAWT

“…To this end, data for a cyclogyro of similar dimensions as the wind turbine, operating in propulsion mode (V wind = 0), is used. This configuration, here denominated IAT21-L3 rotor, was analysed as a part of a major European ongoing project, which aims to develop the cyclogyro technology as a mean of propulsion for small and medium size aircraft [12,[15][16][17][18][19]. It is obvious that the results obtained for the IAT21-L3 rotor does not faithfully represent the features of a VAWT, since in propulsion mode energy is being provided and not extracted from the flow.…”

Analytical modeling of a cyclorotor in hovering state

“…In order to verify its generality, the equation was tested using data from alternative rotors. 22,36 These rotors are different in size and maximum pitch angle from the first rotor that was used to determine equation (28). Figure 20 shows a slope value of E at different pitching conditions as a function of rotating speed.…”

“…Thrust coefficient as a function of rotor angular velocity, comparison between experimental and analytic results-IAT21 case 36. …”

“…30,Power coefficient as a function of rotor angular velocity, comparison between experimental and analytic results, Bosch case. 30,Power coefficient as a function of rotor angular velocity, experimental, and analytic results-IAT21 case 36. …”