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Entry heat transfer tests of the 0.006-scale space shuttle orbiter model (50-0) in langley research center freon tunnel at mach 6 (oh45)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Foust, J. W. |
| Copyright Year | 1975 |
| Description | Results are presented of heat transfer tests of a 147B configuration orbiter model (50-0) conducted in the NASA Langley Research Center Freon Tunnel (LRC/CF4). These tests were conducted at a nominal Mach number of 6, and at Reynolds numbers of 0.3 and 0.5 x 1,000,000 per foot. The objectives of the tests were to determine the effects of the low freon specific heat ratio, gamma, on the heating distributions and to determine the impingement of the orbiter bow shock on the wing. The data presented include thin skin heat transfer data (tabulated data and plotted data). |
| File Size | 47846251 |
| Page Count | 228 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760008156 |
| Archival Resource Key | ark:/13960/t8dg1hv29 |
| Language | English |
| Publisher Date | 1975-12-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Tables Data Shock Waves Hypersonic Reentry Hypersonic Speed Scale Models Aerodynamic Heat Transfer Bow Waves Freon Wind Tunnel Tests Hypersonic Heat Transfer Space Shuttle Orbiters 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 |
