复杂外形飞行器压力分布CFD数值模拟与试验结果比较  

Comparison of numerical simulation and wind tunnel test in pressure distributions analysis for complicated configuration vehicles

作　　者：李海东[1] 梁强[1] 史晓鸣[1] 杨炳渊[1] 

机构地区：[1]上海航天技术研究院第八设计部,上海200233

出　　处：《应用力学学报》2013年第5期707-713,802,共7页Chinese Journal of Applied Mechanics

基　　金："十一五"航天支撑技术项目(617010602);国家自然科学基金(90716001)

摘　　要：为观察粘性效应对物面压力分布的影响,并验证CFD数值模拟方法的计算结果,设计了翼-身-舵组合体模型,利用航天空气动力技术研究院的FD-20炮风洞,在马赫数Ma分别取6、8且攻角α分别取0o、10o、20o的条件下进行了风洞测压试验,同时用Euler方程和N-S方程计算了模型的表面压力并与试验结果进行了比较。结果表明:除少数测点外,弹身、弹翼、舵面及弹身-弹翼干扰区的Euler方程和N-S方程计算结果都比较一致,除了攻角α=20°时的弹翼外,计算结果都与试验结果吻合较好。攻角α=20°的极小展弦比三角弹翼,由于侧前缘脱涡等分离现象的存在,实验值普遍高于计算值10%-15%,但变化趋势一致。因此,在采用CFD数值模拟与工程计算相结合的方法进行气动加热或非定常气动力的计算中,采用Euler方程代替N-S方程求解边界层外缘参数和当地流参数是合理的。To evaluate the viscosity effect on the wall pressure's distribution,and to validate the results of the CFD numerical simulation,a wing-fuselage-rudder model is proposed and tests of pressure measuring in the wind tunnel are carried out with Ma=6,8 at α=0o,10o,20o.Furthermore,the wall pressures are calculated respectively by the Euler equation and the N-S equation for the comparison between the results of numerical simulation and wind tunnel tests.The results show that the computed results by the Euler equation and the N-S equation agree with each other except a few test points,and they are in accordance with the test results mostly.At α=20o there is some difference in the minimal aspect ratio wing because of the flow separation,such as the falling off of the vortex in the side leading-edge of the wing.The test results are 10%-15% higher than the computed results,but they are consistent in the trend.So when the method of CFD is combined with engineering formulas to compute aerodynamic heating and unsteady aerodynamic forces,the Euler equation demonstrates good numerical precision for the local flow parameters and the ones outside the boundary layer.

关 键 词：飞行器 压力分布 风洞试验 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]