高速飞行器减阻杆槽道组合构型减阻防热特性研究  

Investigation on drag and heat flux reduction induced by a novel combinational spike and channel concept for high speed vehicles

作　　者：张帅 郭建 戴梧叶 ZHANG Shuai;GUO Jian;DAI Wuye(Beijing Aerospace Technology Institute,China Aerospace Science and Industry Corporation Limited,Beijing 100074,China;National Key Laboratory of Aerospace Flight Technology,China Aerospace Science and Industry Corporation Limited,Xiongan Hebei 071700,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]中国航天科工集团有限公司北京空天技术研究所,北京100074 [2]中国航天科工集团有限公司空天飞行技术全国重点实验室,河北雄安071700 [3]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2023年第12期3063-3072,共10页Journal of Aerospace Power

摘　　要：针对高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槽道组合构型。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Navier-Stokes方程,对组合构型的流场进行了数值模拟,并分析了减阻防热特性以及其影响因素。数值结果表明:相较于单一减阻杆,引入槽道后,侧向排气将分离激波推离减阻杆,飞行器主体再附激波强度明显减弱,组合构型减阻防热特性显著提高;槽道收敛半角越大,侧向排气孔位置越靠近减阻杆中部,构型减阻防热效果越好;随着飞行动压的增加,构型减阻防热性能不断提高。在研究范围内,收敛半角为60°,侧向排气孔位于减阻杆中部的组合构型减阻防热总体效果最好,并且在动压在30.15 kPa时达到最佳,相比单一减阻杆,飞行器主体壁面热流峰值降低33.84%,总阻力降低14.44%。For the drag and heat flux reduction of high speed vehicles,a novel combinational spike and channel concept was proposed.The high pressure air behind the bow shock flowed into the channel at the head of the spike,and then sprayed out through the lateral jet near the middle of the spike.Based on the SST k-ωturbulence model,the two-dimensional axisymmetric Reynolds average Navier-Stokes equations were solved by the finite volume method,and the flow field of the combinational configuration was numerically simulated.Compared with the single spike,with the introduction of the channel,the lateral jet pushed the separated shock wave away from the spike,and the intensity of the reattachment shock wave was significantly weakened,thus improving the drag and heat flux reduction efficiency.The influencing factors of the combined configuration were analyzed;the larger convergent half angle of the channel indicated the closer location of the lateral jet to the middle of the spike,and the better overall drag and heat flux reduction result of this configuration.With the increase of dynamic pressure,the drag and heat flux reduction performance of the configuration was continually improved.In the research range,the combined configuration in which the convergent half angle was 60°and the lateral jet was located at the middle of the spike had the best overall result of drag and heat flux reduction,and the result reached the best when the dynamic pressure was 30.15 kPa.Compared with the spike,the peak value of heat flux along the blunt body wall was reduced by 33.84%and the total drag of the configuration was reduced by 14.44%.

关 键 词：高速飞行 气动减阻 气动防热 减阻杆 槽道 

分 类 号：V423.6[航空宇航科学与技术—飞行器设计]