低亚声速火箭橇尾流场特性分析  

Analysis of wake flow characteristics for low subsonic rocket sled

作　　者：房明 孙建红[1] 王从磊 余元元[1,3] 张延泰 

机构地区：[1]南京航空航天大学,江苏南京210016 [2]中航工业宏光空降装备有限公司,江苏南京210022 [3]航空防护救生技术航空科技重点实验室,湖北襄阳441003

出　　处：《空气动力学学报》2017年第6期897-901,共5页Acta Aerodynamica Sinica

基　　金：航空科学基金(20142952026);江苏省高校优势学科建设工程资助项目

摘　　要：采用三维不可压Navier-Stokes方程和Realizable k-ε湍流模型,对低亚声速条件下火箭橇试验的流场进行数值模拟,得到了有/无护板火箭橇的流场特性,并对比分析了火箭橇尾流场与飞机尾流场。结果表明,60~90m/s速度条件下,火箭橇受到的气动阻力约为自重的4.8%~8.6%,阻力系数约为0.65,气动升力仅为自重的0.84%~1.9%,升力系数约为-0.005,动力学分析中可以忽略气动升力的影响。不同来流速度下,尾流探测区的无量纲流向速度差值小于8%,无量纲压力差值小于0.5%。低亚声速情况下,来流速度对尾流场特性的影响可以忽略。此外,火箭橇尾流场结构与飞机尾流场结构具有较好的相似性,满足相关速度条件下的动态试验要求。The three-dimensional （3D ） flow field around a rocket sled system in low subsonictesting velocities was simulated through 3D incompressible Navier-Stokes equations and the Realizable hs turbulence model. The wake flow characteristics of the rocket sled with and without the extension plate were obtained at different free stream velocities . Moreover, the difference of the wake flow fields were compared and analyzed between the rocket sled and the aircraft . Results showthat the dynamic drag is about 4. 8 % ？8. 6 % of the total weight of the rocket sled system corresponding to a drag coefficient about 0. 65 for the free strthe range of 60 m/s to 90 m /s. The aerodynamic lift force,which is negative, is merely 0. 84% ~ 1.9% of the total weight,and the lift coefficient is just -0. 005, suggesting that the effect of the aerodynamic lift can be omitted in the kinetic analysis of this rocket sled system. The dimensionless velocity difference in the detection location is less than 8 %,and the dimensionlesspressure difference is less than 0. 5%. These differences indicate that the influence of the velocity on the wake flow field can be neglected. In addition, the wake flow fields are similar according tothe comparison of the wake field between the rocket sled system and the aircraft . This similarity satisfies the requirement of the experimental test .

关 键 词：尾流 气动力 火箭橇 低亚声速流动 阻力系数 

分 类 号：V416.8[航空宇航科学与技术—航空宇航推进理论与工程] V211.3