• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>International Journal of Mechanical Engineering Education >Design, fabrication, and realization of a supersonic wind tunnel for educational purposes
【24h】

Design, fabrication, and realization of a supersonic wind tunnel for educational purposes

机译：用于教育目的的超音速风洞的设计，制造和实现

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The supersonic wind tunnel is an indispensable facility for basic education in any course that covers compressible flows and one of the main pillars of any aerodynamic laboratory. The introduction of a supersonic wind tunnel at the aerodynamics laboratory of the Aerospace Engineering Department at Cairo University had often been postponed and was hindered by a lack of funds for the purchase of foreign equipment and expertise. Thoughts therefore turned to building such facility instead of buying it, substituting high-tech and complex foreign equipment for locally produced equipment, and 'thinking out of the box' to make the most use of available resources, even when this led to some unconventional applications. An extensive scheme for the design, fabrication, and realization of a multi-Mach number (M= 1.5, 2, and 2.5) supersonic wind tunnel for laboratory experiments is proposed in this paper. The proposed scheme is simple, detailed and multi-level; it starts by utilizing one-dimensional isentropic flow theory for the conceptual design phase and makes full use of computational fluid dynamics at the detailed design phase. This ensured that we had a working design before we embarked on the manufacture of any components, which would have been costly to modify had there been any design error. A parametric study has been carried out for a number of design parameters, using numerical simulations. After the design and fabrication, a number of successful standard textbook experiments, for Mach number 2, were carried out as validation for the proposed scheme. The results showed good agreement with the theoretical predictions.
机译：超音速风洞是基础课程中必不可少的设施，涵盖可压缩流和任何空气动力学实验室的主要支柱之一。在开罗大学航空工程系的空气动力学实验室引入超音速风洞通常被推迟，并且由于缺乏购买外国设备和专业知识的资金而受到阻碍。因此，人们的想法转向建造这样的设施，而不是购买它，用高科技和复杂的外国设备替代本地生产的设备，并“开箱即用”以充分利用可用资源，即使这导致了一些非常规的应用。本文提出了一种用于实验室实验的多马赫数（M = 1.5、2和2.5）超音速风洞的设计，制造和实现的扩展方案。该方案简单，详细，多层次；首先在概念设计阶段利用一维等熵流理论，然后在详细设计阶段充分利用计算流体动力学。这确保了我们在着手制造任何组件之前就已经有了一个可行的设计，如果存在任何设计错误，修改该组件的成本将很高。使用数值模拟已经对许多设计参数进行了参数研究。在设计和制造之后，对2号马赫数进行了许多成功的标准教科书实验，以验证所提出的方案。结果与理论预测吻合良好。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号