• 主题
高级搜索  >
历史搜索 清空历史
首页> 美国政府科技报告 >Development of a Computer Code for Calculating the Steady Super/Hypersonic Inviscid Flow around Real Configurations. Volume 1: Computational Technique
【24h】

Development of a Computer Code for Calculating the Steady Super/Hypersonic Inviscid Flow around Real Configurations. Volume 1: Computational Technique

机译：计算实际配置周围稳态超高/超音速非线性流的计算机程序的开发。第1卷：计算技术

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A numerical procedure has been developed to compute the inviscid super/hypersonic flow field about complex vehicle geometries accurately and efficiently. A second order accurate finite difference scheme is used to integrate the three dimensional Euler equations in regions of continuous flow, while all shock waves are computed as discontinuities via the Rankine Hugoniot jump conditions. Conformal mappings are used to develop a computational grid. The effects of blunt nose entropy layers are computed in detail. Real gas effects for equilibrium air are included using curve fits of Mollier charts. Typical calculated results for shuttle orbiter, hypersonic transport, and supersonic aircraft configurations are included to demonstrate the usefulness of this tool. (Author)

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