An active control method for reducing sonic boom of supersonic aircraft

Sonic boom reduction has been an urgent need to develop the future supersonic transport, because of heavy damages noise pollution. This paper provides active control method for aircraft reduce sonic boom, wherein a suction slot near leading edge and injection trailing on airfoil surface are opened, mass flow sucked in is equal injected edge. The diamond 566 airfoils adopted as baseline verify capability method, effects location, rate attack angle ground signature, maximum overpressure, drag coefficients ratio lift studied detail. results show that proposed can significantly intensity more sensitive than Applying this (NACA0008) airfoil, when 6.5 kg/s(7.5 kg/s), value positive overpressure decreased by 12.87%(12.85%), negative 33.83%(56.77%) coefficient 9.50%(10.96%). It be seen great benefits useful reference designing new generation lower aircraft.