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Aerodynamic pressures and heating rates on surfaces between split elevons at mach 6.6
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hunt, L. Roane |
| Copyright Year | 1988 |
| Description | An aerothermal study was performed in the Langley 8-Foot High Temperature Tunnel at Mach number 6.6 to define the pressures and heating rates on the surfaces between split elevons similar to those used on the Space Shuttle. Tests were performed with both laminar and turbulent boundary layers on the wing surface upstream of the elevons. The flow in the chordwise gap between the elevons was characterized by flow separation at the gap entrance and flow reattachment at a depth into the gap inversely proportional to the gap width. The gap pressure and heating rate increased significantly with decrease of elevon gap width, and the maximum gap heating rate was proportional to the maximum gap pressure. Correlation of the present results indicate that the gap heating was directly proportional to the elevon windward surface pressure and was not dependent upon whether the boundary layer on the windward elevon surface was laminar or turbulent. |
| File Size | 11132938 |
| Page Count | 84 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19890003451 |
| Archival Resource Key | ark:/13960/t6h17x60z |
| Language | English |
| Publisher Date | 1988-12-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Elevons Hypersonic Flight Split Flaps Reattached Flow Turbulent Boundary Layer Laminar Boundary Layer Aerodynamic Heating Flow Distribution Wind Tunnel Tests Separated Flow Aerothermodynamics Mach Number Dynamic Pressure 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 |
