针对高超声速飞行器减阻防热问题，提出了一种减阻杆头部开槽进气、中部侧向排气的减阻杆-双盘-槽道组合构型。在飞行高度30 km、来流马赫数6条件下，基于SST k-ω湍流模型，采用有限体积法求解了二维轴对称雷诺平均N-S方程，对组合构型的流场进行了数值模拟，并分析了其减阻防热特性。相比减阻杆-单盘构型，减阻杆-双盘构型减阻防热效果更好，而减阻杆-双盘-槽道构型可以进一步提高减阻防热效果。进行了组合构型的影响因素分析，数值仿真结果表明，在研究参数范围内，侧向排气孔靠近两个气动盘中间位置、第二个气动盘直径较大的构型减阻防热总体效果较好。相比减阻杆-单盘构型，较优构型的总阻力系数降低了24.70%，钝体壁面斯坦顿数峰值降低了53.63%。

In order to reduce the drag and heat flux of the hypersonic vehicles， a novel combinational spike with double aerodisks and channel concept has been proposed. The air behind the bow shock flows into the channel at the head of the aerodisk， and then sprays out through the lateral jet in the middle of the spike. The two-dimensional axisymmetric Reynolds-averaged Navier-Stokes （RANS） equations coupled with the shear stress transport （SST） k-ω turbulence model are solved by finite volume method. The flow field around the combinational configuration is simulated and the drag and heat flux reduction effect is investigated under the flying altitude of 30 km and incoming Mach number of 6. Compared with the spike with single aerodisk， the spike with double aerodisks has better drag and heat flux reduction effect， while the combinational spike with double aerodisks and channel configuration can further improve the effect. The influencing factors of the combinational configuration on the flow field， drag and heat flux reduction effect are investigated thoroughly. The numerical results reveal that， within the research parameters， when the location of the lateral jet is close to the middle of the two aerodisks and the second aerodisk has a larger diameter， the drag and heat flux reduction effect becomes better. Compared with the spike with single aerodisk， the total drag coefficient of the configuration is reduced by 24.70%， and the peak value of Stanton number along the blunt body surface is reduced by 53.63%.

V411.4