CRM-HL 几何结构

本网站目前正在建设中。

This website is currently under construction.

请参阅完整的美国国家航天局（NASA）通用研究模型（Common Research Model）网站以获取最新信息。

Please see the full NASA Common Research Model website for current information.

CRM-HL 几何结构

CRM-HL Geometry

相关文件与数据

Related Files and Data

下方是参考几何结构的 step 文件链接。Excel 列表包含了每个文件中对象的描述。您可以点击下方的链接或 Excel 文件中的链接来下载单个文件。

Below are links to the step files for the reference geometry. The Excel list contains the description of the objects in each file. You can click the links below or the links in the Excel file to download the individual files.

这些模型是将参考几何结构组装而成的完整配置。每个文件都包含一个代表半架飞机的实体。并非所有可能的配置都以这种格式提供，但可以根据需要生成。

These models are assemblies of the reference geometry into full configurations. Each file contains a solid representing the half airplane. Not all possible configurations are available in this format, but can be generated as needed.

请注意，尽管这些几何结构是水密的，但它们不一定适用于流体动力学（Computational Fluid Dynamics，CFD）研究。考虑到风洞建模，模型中存在一些小间隙，在构建网格之前应将其密封，以确保高质量的求解结果。部分可用于 CFD 目的的模型可在“特定模型几何结构”子部分或通过 AIAA 高升力预测研讨会（AIAA High Lift Prediction Workshop）找到。

Note that although these geometries are water tight, they aren’t necessarily appropriate for Computational Fluid Dynamics studies. Several small gaps are present for wind tunnel modeling considerations and should be sealed prior to building grids to ensure a high quality solution. Some models available for CFD purposes can be found in the Model Specific Geometry subsection or through the AIAA High Lift Prediction Workshop.

以下文件适用于 NASA 2.7% 比例全跨度模型和 NASA 5.2% 比例半跨度 CRM-HL 模型。这些几何结构基于参考 CRM-HL 几何结构，并因尺寸限制进行了微小改动。

The files below are for the NASA 2.7% scale full span and the NASA 5.2% scale semispan CRM-HL models. These geometries are based on the reference CRM-HL geometry with minor changes due to size constraints.

**2.7% 比例全跨度着陆和起飞 CAD 文件的最新版本已于 2025 年 7 月 10 日上传**。

**Latest version of the 2.7% scale full span landing and takeoff CAD files were uploaded July 10, 2025**.

下方文件（3001000_fullspan_configs）是一个 zip 压缩包，其中包含用于 2.7% 比例 NTF 模型的着陆和起飞配置的 igs、step 和 x_t 文件。

The file below (3001000_fullspan_configs) is a zip file that contains igs, step and x_t files for both the landing and takeoff configurations of the 2.7% scale NTF model.

***请注意：在风洞模型上，当起落架被移除时，机翼下侧会留下一个空腔。

***Please note: on the wind tunnel model, when the landing gear is removed, there is a cavity left in the underside of the wing.

2p7_fullspan_configs

2p7_fullspan_configs

NASA5p2_CRMHL_LDG_V02_CATPart

NASA5p2_CRMHL_LDG_V02_CATPart

NASA5p2_CRMHL_LDG_V02_stp

NASA5p2_CRMHL_LDG_V02_stp

NASA5p2_CRMHL_LDG_V02_igs

NASA5p2_CRMHL_LDG_V02_igs

德国航空航天中心（DLR）利用 RANS CFD 方法为 CRM-HL 设计了一种短舱变体。设计特别关注了减轻短舱外侧上部的早期流动分离，该分离会影响主翼上的气流。在此背景下，DLR 短舱的设计中加入了一个短舱脊（nacelle chine）。带有 DLR 短舱的 CRM-HL 改型模型旨在代表一种在高升力配置下具有空气动力学效率的运输机，并被命名为 CRM-HL DLR 配置。DLR 短舱的设计旨在实现与 CRM-HL 现有组件的独立交叉研究。

The German Aerospace Center (DLR) designed a nacelle variant for the CRM-HL by using RANS CFD methods. Special attention was paid to the mitigation of early flow separations on the upper outer nacelle, which affects the flow on the main wing. In this context, a nacelle chine has been included in the design of the DLR nacelle. The modified model of the CRM-HL with the DLR nacelle is supposed to represent an aerodynamically efficient transport aircraft in high-lift configuration and is designated as CRM-HL DLR configuration. The DLR nacelle was designed to enable separate cross investigations with the existing components of the CRM-HL

DLR 短舱、挂架和短舱脊变体的几何结构如下。

The geometry for the DLR nacelle, pylon and chine variant is below.