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Effect of geometry on the nose-region flow-field of shuttle entry-configurations
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Bertin, J. J. Faria, H. T. |
| Copyright Year | 1973 |
| Description | In order to determine the convective heat-transfer distribution for the nose region of the space shuttle entry configurations, a three-dimensional flow-field is described which may include extensive regions of separated flow. Because of the complexity of the flow field for the nose region, experimental data are needed to define the relation between the nose geometry and the resultant flow field. According to theoretical solutions of the three-dimensional boundary layer, the boundary layer separates from the leeward generator of a blunted cone at an alpha equal to the cone half-angle. Separation results from the transverse pressure gradient, i.e., the velocity derivative due to crossflow. The boundary layer limiting streamlines converge toward the singular point of sep aration. The separated region is bounded by an ordinary line of separation. |
| File Size | 4401913 |
| Page Count | 43 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730024049 |
| Archival Resource Key | ark:/13960/t9w13tx96 |
| Language | English |
| Publisher Date | 1973-08-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Convective Heat Transfer Nose Cones Three Dimensional Flow Atmospheric Entry Space Shuttles Flow Distribution 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 |
