Aircraft design is an iterative process that requires an estimation of aerodynamic characteristics including drag and lift coefficients, stall behavior, velocity, and pressure profiles repeatedly, especially in the conceptual design phase. PanAir is a high-order aerodynamic panel method-based algorithm developed as a part of the Public Domain Aeronautical Software program mostly with NASA sponsorship. It is based upon potential flow theory and is used to numerically compute lift, induced drag, and moment coefficients of the aircraft in both subsonic and supersonic flight regimes. Quoting from developers it is the most versatile and accurate of all the linear theory panel codes. PanAir is a classical software that requires geometric data as an input in the form of a PanAir-compatible format; however, commonly used Computer-Aided Design Software packages no longer conform to the PanAir input format. Likewise, PanAir produces its output in a PanAir-specific output file which is not compatible with commonly used visualization software. The input geometry required by PanAir and its output, therefore, involves significant manual preand post-processing using intermediary software. The work proposed here is an automated pre and post-processor to be used together with PanAir. With the environment proposed in this work, manipulation of input and output data using several intermediary software to and from PanAir is bypassed successfully. The proposed environment is validated over a Cessna 210 aircraft geometry with a modified NLF (1)-0414 airfoil. The aircraft is numerically analyzed using PanAir together

翻译：飞机设计是一个迭代过程，尤其在概念设计阶段需要反复估算阻力系数、升力系数、失速特性、速度及压力分布等气动特性。PanAir是一种基于高阶气动面元法的算法，作为公共领域航空软件计划的一部分开发，主要由NASA资助。该算法基于势流理论，可用于数值计算飞机在亚声速和超声速飞行状态下的升力系数、诱导阻力系数和力矩系数。据开发者所述，它是所有线性理论面元程序中最通用且最精确的。PanAir是一款经典软件，需要以兼容格式输入几何数据；然而，当前常用的计算机辅助设计软件包已不再符合PanAir输入格式要求。同样，PanAir生成的输出文件格式专有，与常用可视化软件不兼容。因此，PanAir所需的输入几何数据及其输出结果需要通过多种中间软件进行大量手动前处理和后处理。本文提出的方案是一种可与PanAir协同使用的自动化前后处理器。通过本文提出的环境，成功绕过了使用多种中间软件处理PanAir输入输出数据的繁琐操作。该环境以配备改进型NLF(1)-0414翼型的塞斯纳210飞机几何模型进行验证，通过PanAir对该飞机进行数值分析。