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Flow visualization of shock-boundary layer interaction
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jurkovich, M. Hingst, W. R. |
| Copyright Year | 1982 |
| Description | Two and three-dimensional shock-boundary layer interaction data were obtained from supersonic wind tunnel tests. These interactions are studied both with and without boundary layer bleed. The data verify computational fluid dynamic codes. Surface static pressure, pitot pressure, flow angularity, and bleed rates, are studied by flow visualization techniques. Surface oil flow using fluorescent dye and laser sheet using water droplets as the scattering material are used for flow visualization. |
| File Size | 880520 |
| Page Count | 8 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820024799 |
| Archival Resource Key | ark:/13960/t1zd2rd42 |
| Language | English |
| Publisher Date | 1982-09-01 |
| Access Restriction | Open |
| Subject Keyword | Two Dimensional Boundary Layer Fluid Dynamics Supersonic Wind Tunnels Shock Loads Fluorescence Flow Visualization Three Dimensional Boundary Layer Boundary Layer Control Bleeding Boundary Layer Flow Shock Tunnels Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
