experimental accuracy in aerodynamic blowing with high aoa for separation suppression

Separation of the boundary layer on the wing can be associated with a decrease in lift and an increase in drag. this phenomenon, observed in various industries such as turbo machines, land and sea transportation, shuttles, and rockets, can have destructive effects and reduce the efficiency of the mentioned systems. it is possible to control the isolated flow with two active and passive methods. in this paper, the active method (similar gas blowing) has been used experimentally to control the flow field around the naca0012 airfoil at a high angle of attack (18 degrees). due to the stability of the airfoil position on the wing (about 42% of the chord with 4% of the chord width), the effect of changing the parameters of air jet blowing speed and air jet blowing angle in controlling the flow around the airfoil has been investigated. finally, the accuracy and reliability analysis of the airfoil experimental test data was performed, and the results were obtained. among the selected wind angles and wind speeds, the best conditions and options were introduced.