Pulsed Jet Characteristics of Circulation Control Airfoil

Abstract

Compared with the steady jet, the mass flow consumed by the pulsed jet is lower, which is of great significance for solving the jet source in the circulation control technology. In order to further study the effects of different parameters on energy consumption and aerodynamic coefficient pulse in pulsed jet, based on the Reynolds average N-S equation, the aerodynamic characteristic calculation and flow field analysis of the circulation control airfoil under the action of pulsed jet are carried out, and the aerodynamic benefit is evaluated with the combination of energy consumption and aerodynamic coefficient fluctuation. The results show that: Pulsed jet is more suitable for use at high angle of attack. By using the combination of pulsed jet and steady jet, good results can be obtained in three aspects: time-averaged lift coefficient, lift coefficient fluctuation and energy consumption. The research results can be used as a reference for guiding the use of pulsed jet in circulation control technology.

Investigation of lift enhancement through circulation control for distributed propulsion

“…Their research revealed that synthetic jets enhance airfoil circulation through affecting the position of the airfoil's trailing vortex and upper surface separation point, indicating that synthetic jets have higher efficiency than previous circulation control devices. In addition, the research on the dual-jet circulation control airfoils by He Yujuan and his collaborators [8], on stable-jet circulation control techniques by Zheng Wuji [9], and on pulsed-jet circulation control techniques by Lei Yuchang and his collaborators [10] have analyzed the circulation control law and aerodynamic characteristics under their respective conditions, and achieved relatively satisfactory results. Zhu Ziqiang [11] summarized the research progress of the circulation control technology and discussed how it could effectively postpone the location of the shock wave according to the results of wind tunnel experiments, thus increasing the stalling angle of attack.…”