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Heat transfer tests of a 0.006-scale thin skin space shuttle model (50-0, 41-t) in the langley research center nitrogen tunnel at mach 19 (ih19)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Walstad, D. G. |
| Copyright Year | 1975 |
| Description | Data are presented from heat transfer tests on an 0.0006-scale space shuttle vehicle in the Langley Research Center Nitrogen Tunnel. The purpose of this test was to obtain ascent heating data at a high hypersonic Mach number. Configurations tested were integrated orbiter and external tank, orbiter alone, and external tank alone. All configurations were tested with and without boundary layer transition. Testing was conducted at a Mach number of 19, a Reynolds number of 0.5 million per foot, and angles of attack of 0, + or - 5, and + or - 10 degrees. Heat transfer data was obtained from 77 orbiter and 90 external tank iron-constantan thermocouples. |
| File Size | 37877204 |
| Page Count | 731 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760008165 |
| Archival Resource Key | ark:/13960/t5dc2t79v |
| Language | English |
| Publisher Date | 1975-11-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance External Tanks Hypersonic Speed Aerodynamic Heat Transfer Thermocouples Reynolds Number Space Shuttles Wind Tunnel Tests Hypersonic Heat Transfer Wind Tunnel Models Nitrogen Space Shuttle Orbiters Mach Number 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 |
