Design and Experiment Study of Coanda Surface at Airfoil Trailing Edge

The flying-wing aircraft has good aerodynamic and stealth performance but poor attitude control capability. The jet circulation control (JCC) technology is the most widely used, which changes circulation by blowing air at the wing trailing edge to form the Coanda effect. The design method of 2D Coanda profile is proposed, which can increase pitch control efficiency obviously. The Coanda profile that matches the jet slot height of 0.30 mm is designed under Mach number 0.6. The flow control mechanism of Coanda profiles with and without steps are analyzed deeply. JCC effect of airfoil including different jet devices under Mach number 0.5 is studied with wind tunnel test and computational fluid dynamics (CFD). The research results indicate that the design method of 2D Coanda profile proposed is feasible and effective. The simulation capability of CFD at jet circulation control is verified further by wind tunnel tests. It can be developed to the research of the flying-wing aircraft without control surfaces based on JCC technology. It is promising to solve attitude control difficulties of the flying-wing layout.