高超声速飞行器钝舵缝隙流动数值模拟研究
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摘要
目前,带缝隙钝舵的缝隙引起的流场结构和气动加热规律变化,还很不明确,需要研究缝隙诱导所形成旋涡的空间分布特征和旋涡运动对物面气动加热的影响规律。通过分析高超声速钝舵缝隙气动加热问题,基于无缝隙钝舵,建立一种带缝隙钝舵简化模型。使用有限体积方法求解可压缩Navier-Stokes方程,通量采用van Leer通量向量分裂方法计算。插值采用MUSCL方法,时间项采用LU-SGS隐式方法。结果表明:无缝隙钝舵流场结构相对简单,带缝隙钝舵流场结构同无缝隙钝舵相比要更为复杂,舵轴上游缝隙内会出现马蹄形涡串结构,相应地在缝隙的上下表面均会出现马蹄形高热流区;受缝隙诱导分离再附流动的影响,在舵轴迎风面以及舵体侧面后部均形成了局部高热流区。
At present, the change of flow field structure and aerodynamic heating law caused by slot blunt fin gap is still unclear, so it is necessary to study the spatial distribution feature of the vortex induced by gap and corresponding relations between the vortex motion and heat-flux distribution. By analyzing the aerodynamic heating problem of hypersonic blunt fin gap, a simplified model of blunt fin gap is established based on the seamless blunt rudder. Compressible Navier-Stokes equation is solved by finite volume method, and Flux is calculated by van Leer flux vector splitting method. Interpolation method employ the MUSCL and LU-SGS implicit method are used for time term. The results show that the flow field structure of seamless blunt rudder will be relatively simple, and the flow field structure of blunt rudder with gap will be more complex than that of seamless blunt rudder. Horseshoe-shaped vortex string structure will appear in the upstream crevice of rudder shaft, and correspondingly horseshoe-shaped high heat flow zones will appear on the upper and lower surfaces of gap; Due to the influence of gap induced separation and reattachment flow, local high heat flow zones will form on the windward side of rudder shaft and the rear side of rudder body.
At present, the change of flow field structure and aerodynamic heating law caused by slot blunt fin gap is still unclear, so it is necessary to study the spatial distribution feature of the vortex induced by gap and corresponding relations between the vortex motion and heat-flux distribution. By analyzing the aerodynamic heating problem of hypersonic blunt fin gap, a simplified model of blunt fin gap is established based on the seamless blunt rudder. Compressible Navier-Stokes equation is solved by finite volume method, and Flux is calculated by van Leer flux vector splitting method. Interpolation method employ the MUSCL and LU-SGS implicit method are used for time term. The results show that the flow field structure of seamless blunt rudder will be relatively simple, and the flow field structure of blunt rudder with gap will be more complex than that of seamless blunt rudder. Horseshoe-shaped vortex string structure will appear in the upstream crevice of rudder shaft, and correspondingly horseshoe-shaped high heat flow zones will appear on the upper and lower surfaces of gap; Due to the influence of gap induced separation and reattachment flow, local high heat flow zones will form on the windward side of rudder shaft and the rear side of rudder body.
引文
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[3] 彭治雨,石义磊,龚红明,等.高超声速气动热预测技术及发展趋势[J].航空学报,2015,36(1):325-345.Peng Zhiyu,Shi Yilei,Gong Hongming,et al.Hypersonic aeroheating prediction technique and its trend of development[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):325-345.(in Chinese)
[4] 李素循.激波与边界层主导的复杂流动[M].北京:科学出版社,2007:68-80.Li Suxun.Complex flow control by shock waves and boundary layers[M].Beijing:Science Press,2007:68-80.(in Chinese)
[5] 陈雄昕,刘卫华,罗智胜,等.高超音速飞行器气动热研究进展[J].航空兵器,2014(6):8-13.Chen Xiongxin,Liu Weihua,Luo Zhisheng,et al.Research advances of aerodynamic heating for hypersonic aircraft[J].Aero Weaponry,2014(6):8-13.(in Chinese)
[6] Tang Guiming,Yu Hongru.Aerodynamic heating in the region of shock and turbulent boundary layer interaction induced by a cylinder[J].Acta Mechanica Sinica,1992,8(3):224-230.
[7] 王世芬,王宇.钝缘舵高超音速湍流分离特性[J].航空学报,1996,17(7):1-6.Wang Shifen,Wang Yu.Turbulent separation features induced by blunt fins in hypersonic flow[J].Acta Aeronautica et Astronautica Sinica,1996,17(7):1-6.(in Chinese)
[8] Tang Guiming.Heating characteristics of blunt swept fin-induced shock wave turbulent boundary layer interaction[J].Acta Mechanica Sinica,1998,14(2):139-146.
[9] 李素循,马继魁,郭孝国.大后掠钝舵高超声速干扰特性实验研究[J].气体物理,2016,1(3):1-5.Li Suxun,Ma Jikui,Guo Xiaoguo.Experimental study of hypersonic interaction flow induce by high sweep fin model[J].Physics of Gases,2016,1(3):1-5.(in Chinese)
[10] 栗继伟,汪球,赵伟.高超声速绕平板直立舵干扰气动热研究[J].中北大学学报:自然科学版,2017,38(5):111-115.Li Jiwei,Wang Qiu,Zhao Wei.Investigation on aerodynamic heating characteristics of hypersonic flat pate/cylinder juncture flow[J].Journal of North University of China:Natural Science Edition,2017,38(5):111-115.(in Chinese)
[11] 李艳丽,李素循.高超声速绕钝舵层流干扰流场特性研究[J].宇航学报,2007,28(6):1472-1477.Li Yanli,Li Suxun.Investigation of interactive hypersonic laminar flow over blunt fin[J].Journal of Astronautics,2007,28(6):1472-1477.(in Chinese)
[12] 朱自强,吴子牛,李津,等.应用计算流体力学[M].北京:北京航空航天大学出版社,1998.Zhu Ziqiang,Wu Ziniu,Li Jin,et al.Applied computational fluid mechanics[M].Beijing:Beihang University Press,1998.(in Chinese)
[13] Van Leer B.Towards the ultimate conservative difference scheme V.A second order sequel to godunov’s method[J].Journal of Computational Physics,1979(32):101-136.
[14] Anderson W K,Thomas J L,van Leer B.A comparison of finite volume flux vector splitting for the Euler equations[J].AIAA Journal,1986,24(9):1453-1460.
[15] Yoon S,LU-SGS implicit algorithm for three dimensional incompressible Navier-Stokes equations with source term[C]//The 9th AIAA CFD Conference,1989.