| タイトル | Wind-US Code Physical Modeling Improvements to Complement Hypersonic Testing and Evaluation |
| 本文（外部サイト） | http://hdl.handle.net/2060/20090027874 |
| 著者（英） | Bhagwandin, Vishal A.; Lankford, Dennis W.; Georgiadis, Nicholas J.; Towne, Charles S.; Engblom, William A.; Nelson, Christopher C.; Power, Greg D.; Yoder, Dennis A. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2009-07-01 |
| 言語 | eng |
| 内容記述 | This report gives an overview of physical modeling enhancements to the Wind-US flow solver which were made to improve the capabilities for simulation of hypersonic flows and the reliability of computations to complement hypersonic testing. The improvements include advanced turbulence models, a bypass transition model, a conjugate (or closely coupled to vehicle structure) conduction-convection heat transfer capability, and an upgraded high-speed combustion solver. A Mach 5 shock-wave boundary layer interaction problem is used to investigate the benefits of k- s and k-w based explicit algebraic stress turbulence models relative to linear two-equation models. The bypass transition model is validated using data from experiments for incompressible boundary layers and a Mach 7.9 cone flow. The conjugate heat transfer method is validated for a test case involving reacting H2-O2 rocket exhaust over cooled calorimeter panels. A dual-mode scramjet configuration is investigated using both a simplified 1-step kinetics mechanism and an 8-step mechanism. Additionally, variations in the turbulent Prandtl and Schmidt numbers are considered for this scramjet configuration. |
| NASA分類 | Aeronautics (General) |
| レポートNO | E-16931
NASA/TM-2009-215615
AIAA-2009-193 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/253169 |
