摘要
数值模拟了带副翼偏转构型的二维、三维亚、跨、超声速来流情况的绕流流场,采用有限体积方法和AUSM+迎风格式数值求解N-S方程,四步龙格-库塔时间推进,湍流模型为Baldwin-Lomax和Spalart-All-maras湍流模型。二维模拟压强分布与实验数据以及CFD软件模拟结果吻合较好。采用交错对接网格,数值模拟了不同副翼偏角和缝隙、来流马赫数、迎角和雷诺数的三维构型流场。通过舵面铰链力矩与实验数据的对比分析表明了该数值方法模拟此类复杂流场的可靠性和舵面铰链力矩计算的有效性。发现并研究了亚声速来流时铰链力矩随迎角的反向变化趋势,初步分析了副翼的缝隙和雷诺数效应。
The flows around 2 D and 3 D wings with ailerons deflected are numerical simulated in cases of subsonic, transonic and supersonic speeds. The Navier-Stokes equations are solved using finite volume method and AUSM＋ scheme, and the four step Range-Kutta method for time marching. Turbulence models used are Baldwin-Lomax and Spalart Allmaras models. The 2-D calculated pressure results coincide well with the experiment data and CFD software simulation results. Using mismatched multiblock grids, the flow fields of 3-D wing with different aileron deflected angles and gaps are simulated at different Mach numbers, angles of attack and Reynolds numbers. The calculated hinge moment values of control surfaces are compared with the experiment data. It is shown that the present numerical method is reliable and can be used as an effective tool for an alyzing such kind of complex flow. The reverse varying trend of the hinge moment with angle of attack in subsonic incoming flow is observed and investigated. The effects of Reynolds number and aileron gap are analyzed primarily.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2007年第3期519-526,共8页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(04A51044)
