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Investigation of configuration effects on entry heating distributions at mach no. equal 8.0 (oh41). [for wind tunnel model of space shuttle orbiter
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gorowitz, H. Derrico, A. White, R. |
| Copyright Year | 1973 |
| Description | Aerodynamic heating data were obtained on 0.006 scale models of four Rockwell International SSV double delta wing Orbiters in the Mach 8 variable density tunnel. A model of two previously tested Rockwell International Orbiters which are identified in the Configuration Description of this report were also tested. Orbiter surfaces were thermally mapped from the laminar through turbulent flight regimes during re-entry. Various modifications were made to model lower surfaces to determine the cause of transition in the vicinity of 3.0 million Reynolds number per foot. Re-entry data were acquired for angles of attack from 25 through 35 degrees at nominal Reynolds numbers per foot of 1.0, 2.0, 2.3, 2.5, 3.0, 3.5, 4.5 and 6.0 million utilizing the phase change paint technique. Launch data were acquired on the model upper surfaces for angles of attack of 0 and -5 degrees at nominal Reynolds numbers per foot of 3.0 and 6.0 million. A total of 70 orbiter heating runs and 6 material sample sphere runs were completed. |
| File Size | 6002681 |
| Page Count | 188 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740002688 |
| Archival Resource Key | ark:/13960/t44r2nx2d |
| Language | English |
| Publisher Date | 1973-09-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Hypersonic Speed Aerodynamic Configurations Data Acquisition Aerodynamic Heating Wind Tunnel Tests Reentry Vehicles Wind Tunnel Models Space Shuttle Orbiters Aerothermodynamics 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 |
