摘要
Sonic boom reduction has been an urgent need for the development of future supersonic transport,because of the heavy damage of noise pollution.This paper provides a novel concept for supersonic aircraft to reduce the sonic boom and drag coefficient,wherein a suction slot near the leading edge and an injection slot near the trailing edge on the airfoil suction surface are opened.To make sure of a zero net mass flux flow control,the mass flow sucked in near the leading edge is equal to the mass flow injected near the trailing edge.The diamond and NACA0008 airfoils are adopted as the baseline airfoil to verify the capability of the proposed design method.The effects of the suction and injection location,the suction and injection slot size,the mass flow rate and the attack angle on the ground boom signature and drag coefficient are studied in detail.The results show that the optimized airfoils with the suction and injection have benefits in both sonic boom reduction and wave drag reduction.And the reduction of the sonic boom intensity is more sensitive to the injection near the trailing edge than the suction near the leading edge.From the viewpoint of aerodynamics,opening the suction and injection slots will have no adverse effect on the aerodynamic performances of the supersonic aircraft and even increase the lift-drag ratio under some circumstances.For energy saving,the suction and injection slots can be selectively opened,which are opened when the supersonic aircraft flies over the city but are closed when the aircraft flies over the sea.
基金
supported by the National Natural Science Foundation of China(Grants No.11732013)
the National Numerical Windtunnel project(NNW2019ZT3-A15).
