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Intersecting shock-wave/turbulent boundary-layer interactions at mach 8.3
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Horstman, K. C. Kussoy, M. I. |
| Copyright Year | 1992 |
| Description | Experimental data for two three-dimensional intersecting shock-wave/turbulent boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat-plate test bed, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure and heat transfer distributions as well as mean flow-field surveys both in the undisturbed and interaction regimes. The data are presented in a convenient form to be used to validate existing or future computational models of these hypersonic flows. The data are also on a 3.5-inch diskette included and are available through E-mail. |
| File Size | 1806181 |
| Page Count | 52 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930015348 |
| Archival Resource Key | ark:/13960/t9v16z99m |
| Language | English |
| Publisher Date | 1992-02-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Boundary Layer Separation Computational Fluid Dynamics Flow Distribution Turbulent Boundary Layer Shock Wave Interaction Pressure Distribution Hypersonic Flow Fins Mathematical Models Heat Transfer Boundary Layer Flow Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
