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Weak incident shock interactions with mach 8 laminar boundary layers. [of flat plate
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kaufman II, L. G. Johnson, C. B. |
| Copyright Year | 1974 |
| Description | Weak shock-wave interactions with boundary layers on a flat plate were investigated experimentally in Mach 8 variable-density tunnel for plate-length Reynolds numbers. The undisturbed boundary layers were laminar over the entire plate length. Pressure and heat-transfer distributions were obtained for wedge-generated incident shock waves that resulted in pressure rises ranging from 1.36 to 4.46 (both nonseparated and separated boundary-layer flows). The resulting heat-transfer amplifications ranged from 1.45 to 14. The distributions followed established trends for nonseparated flows, for incipient separation, and for laminar free-interaction pressure rises. The experimental results corroborated established trends for the extent of the pressure rise and for certain peak heat-transfer correlations. |
| File Size | 3191117 |
| Page Count | 47 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750004171 |
| Archival Resource Key | ark:/13960/t8ff8jj7q |
| Language | English |
| Publisher Date | 1974-12-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Boundary Layer Separation Shock Waves Laminar Boundary Layer Flat Plates Heat Transfer 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 |
