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Cfd validation experiment of a mach 2.5 axisymmetric shock-wave boundary-layer interaction
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Davis, David O. |
| Copyright Year | 2015 |
| Description | Preliminary results of an experimental investigation of a Mach 2.5 two-dimensional axisymmetric shock-wave/boundary-layer interaction (SWBLI) are presented. The purpose of the investigation is to create a SWBLI dataset specifically for CFD validation purposes. Presented herein are the details of the facility and preliminary measurements characterizing the facility and interaction region. The results will serve to define the region of interest where more detailed mean and turbulence measurements will be made. |
| File Size | 1610555 |
| Page Count | 11 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150015493 |
| Archival Resource Key | ark:/13960/t7hq8z62w |
| Language | English |
| Publisher Date | 2015-07-26 |
| Access Restriction | Open |
| Subject Keyword | Superonic Flow Turbulence Modeling Shock-wave/boundary Layer Interaction Turbulent Flow Supersonic Speed Computational Fluid Dynamics Reynolds Number Flow Measurement Shock Wave Interaction Boundary Layers Mach Number Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |