针对单一减阻杆构型在有迎角来流条件下降热效果急剧下降的问题，提出了减阻杆和环形喷流组合构型的降热方案，对减阻杆和环形喷流组合构型进行不同来流和喷流条件下的数值模拟，得到了模型流场和壁面热流分布。研究结果表明：在组合构型的流场中，喷流受减阻杆后低压区的影响，未直接与自由来流作用，喷流压比从0.05至0.40，组合构型流场未出现长穿透模态和短传透模态转变，流场结构更为稳定；喷流包覆了减阻杆和钝头体壁面，再附激波和分离激波被推离壁面。0°迎角来流条件下，小喷流压比也有好的降热效果，喷流压比为0.05可以使减阻杆构型钝头体的壁面热流峰值降低到原来的一半以下；单一减阻杆构型在有迎角来流条件下，分离激波和再附激波直接作用在钝头体壁面上，钝头体壁面热流急剧上升。组合构型在有迎角来流条件下有明显的降热效果；随着迎角的增加，喷口处的背压升高，喷流对流场的干扰效应减弱，达到相同的降热效果需要更大的喷流压比；相同的喷流压比下，在再附着点前喷流，喷流膨胀更完全，降热效果更好；减阻杆和环形喷流组合构型相对于单一减阻杆构型，在小喷流压比下减阻效果增强。

Drag reduction spikes can reduce the heat flow of the supersonic aircraft head at 0-degree angle of attack. However， the heat reduction effect sharply drops with the increasing angle of attack. To solve this problem， we propose the heat reduction scheme of the combination of annular jet and drag-reduction spike. Numerical simulations of this scheme under different inflow and jet conditions are carried out to obtain the flow filed and the wall heat flow distribution. The conclusions are as follows： in the flow field of the combined scheme， affected by the low-pressure area behind the drag-reduction spike， the jet does not directly interact with the free stream， and there is no transition between the long and short penetration modes， with the jet pressure ratios ranging from 0.05 to 0.40. Thus， the flow field structure of the reverse jet is more stable. Furthermore， the drag-reduction spike and the blunt body are coated by the reverse jet. The attached shock wave and separated shock wave are pushed away from the wall. The numerical results show that under the condition of 0° angle of attack， a small jet pressure ratio also has a good heat reduction effect. When the jet pressure ratio is 0.05， the peak heat flow on the blunt body wall can be reduced to smaller than half of the original value. The attached shock wave and separated shock wave generated by a single drag reduction spike at an angle of attack act directly on the blunt head wall， resulting in a sharp rise in the heat flow through the wall. The combined scheme has clear heat reduction effect with an angle of attack. With the increase of the angle of attack， the back pressure at the nozzle increases， while the interference effect of the jet on the flow field decreases. To achieve the same heat reduction effect， a larger jet pressure ratio is required. At the same jet pressure ratio， the jet flow before the reattachment point can make the jet flow expand more completely and reduce heat more effectively. At small jet pressure ratios， the drag reduction effect of the combined configuration of the drag reducing rod and the annular jet is enhanced compared to the single drag reducing rod.