随着高性能计算机的发展，CFD已成为飞行器设计和流场分析不可缺少的重要手段，风洞试验与飞行数据的天地相关性问题正是其中一项重要的研究内容，X-37B作为继航天飞机之后美国发展的最成功的可跨大气层在轨飞行器，从气动特性角度分析其大气层内飞行走廊的状态对中国类似航天器的研制具有重要的借鉴意义。首先，对计算类X-37B布局飞行器的网格无关性及网格修正开展了研究，在此基础上提出的网格规模影响修正方法对该类飞行器的计算结果修正经过验证是可信的；然后，分别对比分析了雷诺数的影响和试验状态支架干扰的影响，完成了基于数值模拟的高空飞行与风洞试验气动特性差异分析。结果表明，网格规模主要对亚声速来流计算状态压差产生的轴向力影响较大，对法向力系数、俯仰力矩系数和纵向压心影响较小；雷诺数对该类飞行器气动特性特别是轴向力系数、阻力系数和升阻比有较大的影响，但随着马赫数的增加，影响特性开始变的非常复杂；由于风洞试验状态支杆存在，亚跨声速来流条件对该类飞行器的底阻影响很大，需要采取一定的方法和手段对支杆影响进行修正。
X-37B is the most successful trans-atmospheric orbital vehicle in the US after the space shuttle. Analyzing the aerodynamic characteristics in its flight corridor can provide significant reference for the development of similar spacecraft in China. With the progress of HPC, CFD has become an important method in aircraft design and flow field analysis, in which the correlation between the flight and ground data is part of the validation function. The grid independence and correction of an X-37B-like aircraft have been studied, followed by the research on the Reynolds number effect and support interference effect. The difference between the high-altitude aerodynamic data and wind-tunnel results are computed and studied. The grid scale has a significant effect on the axial drag in the subsonic flow, and a minor effect on the normal force and pitching moment. The Reynolds number has a significant effect on the axial force, drag force and lift-drag ratio, while the effect becomes complex as the Mach number increases. The presence of the support sting in the wind tunnel has a remarkable effect on the aircraft base drag under subsonic and transonic inflow conditions, and correction of the support effect should be modified in a certain way.
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