Software Testing: VSPAERO

Purpose - Test the aerodynamic analysis code VSPAERO, which is part of OpenVSP from NASA. Apply VSPAERO to calculate the lift curve slope and the span efficiency factor of straight wings (for various aspect and taper ratios) as well as the induced drag of box wings (for various h/b-ratios) relative to their reference wing. --- Methodology - VSPAERO results are compared with results from analytical equations, wind tunnel measurements, and results produced with other aerodynamic codes. --- Findings - VSPAERO offers correct and reliable results, if the simulation is set up with care. The user must always keep an eye on model discretization and refinement, flow conditions, and number of iterations. The Vortex Lattice Method (VLM) and the panel method are best used for different purposes. The VLM shows shorter simulation time and produces reliable results. The panel method is more complicated to use. Numerical results are also good. In addition, the panel method can be used better to visualize flow phenomena. Hoerner's simple approach to induced drag estimation can be used to approximate results of the VLM and the panel method, if a simple correction factor is applied. --- Research Limitations - Most of the tests of VSPAERO have been done with a simple wing geometry, as such much simpler than a full aircraft geometry. --- Practical Implications - VSPAERO can be used with relative ease. It can also be used to show flow phenomena on full aircraft geometry. --- Originality - Repeating simple calculations done many times before does not sound original, but doing this with the relatively new software VSPAERO offering the VLM as well as the panel method seems to be original after all.研究目的：测试隶属于美国国家航空航天局（NASA）OpenVSP平台的气动分析代码VSPAERO。使用VSPAERO计算不同展弦比和锥度比的平直机翼的升力曲线斜率与展向效率因子，以及不同h/b比的盒式机翼相对于参考机翼的诱导阻力。 研究方法：将VSPAERO的计算结果与解析方程推导结果、风洞实测结果以及其他气动代码生成的结果进行对比验证。 研究发现：若谨慎设置仿真参数，VSPAERO可输出准确且可靠的计算结果。使用者需始终关注模型离散化与细化程度、流动条件以及迭代次数。涡格法（Vortex Lattice Method, VLM）与面元法各有适用场景：VLM的仿真耗时更短，且可生成可靠结果；面元法的操作流程更为复杂，但其数值计算结果同样优秀。此外，面元法更适用于流动现象的可视化。若引入简单修正因子，Hoerner提出的诱导阻力估算简易方法可用于近似VLM与面元法的计算结果。 研究局限性：当前针对VSPAERO的多数测试均采用简化机翼几何构型，其复杂度远低于完整飞机的几何模型。 实际应用价值：VSPAERO的使用难度相对较低，同时可用于完整飞机几何构型的流动现象可视化分析。 研究创新性：尽管重复开展此类已有多次的简易计算看似缺乏创新性，但针对同时集成涡格法与面元法的较新型软件VSPAERO开展此类验证研究，仍具备一定的原创价值。