弧形翼-身组合体绕流流场数值模拟及实验研究  

Experimental Study and Numerical Simulation of Flow Field over Wrap-around Fin-body Combination

作　　者：郑健[1] 周长省[1] 鞠玉涛[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《南京理工大学学报》2012年第3期505-510,共6页Journal of Nanjing University of Science and Technology

摘　　要：为了研究标准技术协作计划(TTCP)弧形翼-身组合体的空气动力学特性,对其在超声速下的三维绕流流场进行了数值模拟。应用雷诺应力湍流模型和平流迎风劈裂法离散格式,对弧形翼-身组合体在Ma∈[2.0,5.5]范围内的超声速绕流流场结构进行了分析。计算分析了弧形翼-身组合体的各气动力系数随马赫数、攻角的变化规律。阐述了弧形翼在零攻角状态下产生自诱导滚转力矩的机理。利用超声速风洞进行了标准TTCP弧形翼-身组合体在Ma=3.0条件下的吹风实验。实验结果与数值模拟结果的计算误差小于10%,验证了所采用数值模拟方法的可信度。To study the aerodynamic characteristics of the technical cooperation program （TYCP） standard wrap-around fin （WAF）-body combination, the three-dimensional supersonic flow over it is numerically simulated. In the range of Ma ∈ [ 2.0,5.5 ], the supersonic flow field structure of the WAF-body combination is analyzed by using the Reynolds stress turbulence model and advection upwind splitting method discrete scheme. The change rules of the WAF-body combination aerodynamic coefficients with Mach numbers, angles of attack are calculated and analyzed. The mechanism of self- induced roll moment produced at zero attack angle is analyzed. The flow tests of the standard TFCP WAF-body combination are conducted in the condition of Ma = 3.0 by a supersonic wind tunnel. The calculation error between the numerical simulation results and wind tunnel test ones is less than 10%, which verifies the credibility of the numerical simulation method.

关 键 词：弧形翼 翼-身组合 流场 雷诺应力湍流模型 平流迎风劈裂法 吹风实验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]