Abstract: The influence of the location and the flux of the exhaust outlet on the supersonic aircraft by CFD method was studied. The optimum location was confirmed, and the research of the influence of angle of attack on exhaust effects was further carried out. The results show that: 1) the main stream has strong interference with the gas discharged by the turbopump, and the separation zone on the aircraft surface increases with the increase of the exhaust volume, resulting in drag increase and lift decrease. 2)the exhaust on the upper and lower surfaces can lead to drag increase, and the drag on the lower surface is larger than that on the upper surface under the same exhaust volume due to the upwind conditions; 3) the exhaust position should be set on the upper surface in order to reduce the drag when the aircraft is at the positive angle of attack; 4) when exhausting on the upper surface, the drag increases gradually with the increase of the angle of attack, but the difference from the reference state decreases gradually with the increase of the angle of attack.