Aerodynamic deceleration is one of the key technologies for aerospace vehicles.The inflatable reentry vehicle can increase its payload by reducing the weight of the return system, which has the obvious ad-vantages of light weight, easy package, large drag area, low ballistic coefficient, and small heat generated by hypersonic air. The NASA's Inflatable Reentry Vehicle (IRV-3) is used as an example to study the flow field numerical calculation of different speeds and attack angles, by using finite volume method. Comparing the viscous flow field numerical model result with the inviscid model, result shows that inviscid model in super-sonic cases can meet certain accuracy requirements, improving the stability and the calculation efficiency. The aerodynamic performances at different speeds and attack angles are also studied. The results indicate that drag coefficient increases with increased much number and then gradually decreases, which reach a maximum value at 5Ma. When the attack angle changes at small angle, the changes of pitching moment coefficient and lift coef-ficient are bigger than the drag coefficient. A proper attack angle can reduce the pitching moment coefficient, which improves the stability of inflatable reentry vehicle. The results of this paper have reference value for de-sign and analysis of inflatable reentry vehicles.%减速是返回式航天飞行器必须面对的关键性问题。充气式返回舱通过降低返回系统的质量增加了有效载荷，具有质量轻、易折叠包装、展开阻力面积大，再入时弹道系数低和产生的气动热量小等优点。文章以美国 NASA 的充气式返回舱（IRV-3）为研究对象，采用有限体积法进行了不同速度和迎角下的流场数值计算。研究对比了充气式返回舱在粘性模型和无粘模型下的流场数值结果，发现无粘模型在超声速情况下能满足一定的精度要求，提高了计算稳定性和计算效率。考察了不同迎角、速度下充气式返回舱的气动性能，结果表明阻力系数随着马赫数增加升高之后再逐渐降低，在Ma=5时气动阻力最大；合适的迎角可以降低俯仰力矩系数，增加返回舱的稳定性；迎角在小角度变化时，俯仰力矩系数和升力系数变化较大，而阻力系数变化较小。文章的研究结果对充气式返回舱的设计及分析有一定参考意义。
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