Abstract: This work has been done in a shock tunnel,in the range M_∞=0.732 ～ 0.817and Re_∞=3 × 10￣7,on different half models:circular arc aerofoils with 12%thickness ratioand supercritical aerofoils with 14%thickness ratio。 The results show that:in comparisonwith solid wall of the model,the porous walls with cavity deepness 1mm or 3mm,and thewall with conduit tubes can reduce the peak of Much Number,adverse pressure gradient, andthe strength of shock wave That means passive control can reduce the drag of an aircrafta...