跨音速三维操纵面嗡鸣数值方法研究  

Relatively Accurate Calculation of 3-D Control Surface Buzz in Transonic Flow

作　　者：史爱明[1] 杨永年[1] 叶正寅[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2006年第5期537-540,共4页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(10432040);航空科学基金(04A53006)资助

摘　　要：在非结构化动态网格耦合欧拉方程求解跨音速非定常流场的基础上,考虑了翼面-操纵面系统的缝隙间网格运动问题。采用中心有限体积法进行空间离散和双时间方法进行时间推进求解非定常欧拉方程。通过与气动力方程的联立求解,在时域内用四步龙格-库塔方法求解结构运动方程。数值分析研究了NA SA三维操纵面嗡鸣标模算例——全翼展操纵面NA SP(N ationalA eroSpace P lane)基本型机翼-操纵面嗡鸣现象,并和风洞实验结果进行了对比,取得了一致的结果,说明了该方法的正确性。Aim. We were the first to apply unstructured dynamic mesh to relatively accurately calculating the effect of gap on 2-D control surface. Now, we apply such technique to relatively accurately calculating the effect of gap on 3-D control surface. Control surface buzz can only be roughly determined without considering the effect of gap. In the full paper, we explain in detail how to apply unstructured dynamic mesh to calculating 3-D control surface buzz; in this abstract, we just add some pertinent remarks to listing the two topics of explanation： （1） method of calculation of unsteady aerodynamics; a finite volume algorithm based on center difference is used to solve the Euler equations; the full implicit dual-time scheme is adopted to treat the unsteady aerodynamic problem; （2） equation of motion of control surface and unstructured dynamic mesh technique ; the subtopics are equation of motion of control surface （subtopic 2.1） and unstructured dynamic mesh technique （subtopic 2. 2）; in subtopic 2. 1, the control surface motion equation is marched by Runge-Kutta method in time domain; in subtopic 2.2, in order to take into account the effect of gap （Fig. 1 and Fig. 2）, the unstructured dynamic mesh technique is introduced to simulate the movement of the control surface; furthermore, in subtopic 2. 2, we also propose some improvements to raise the capability of well-known unstructured dynamic mesh technique. Finally we took NASP （National AeroSpace Plane） wing with 3-D full-span control surface as numerical example. The results of calculation with our method, given in Figs. 3 through 5 in the full paper, show preliminarily fairly good agreement with test data given in Ref. 9 by Paker et al.

关 键 词：NASP机翼 嗡鸣 非定常流场 非结构化动态网格 

分 类 号：V212.2[航空宇航科学与技术—航空宇航推进理论与工程]