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Heat transfer tests of an 0.006-scale thin-skin space shuttle thermocouple model (141-ot) in the langley research center freon tunnel at m-6 (ih18). [wind tunnel tests
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Walstad, D. G. |
| Copyright Year | 1976 |
| Description | Ascent heating data were obtained at conditions simulating real gas effects at hypersonic Mach numbers. The configurations tested were Orbiter alone, external tank alone, and mated Orbiter and external tank. A boundary layer trip investigation was conducted for all configurations. The test was conducted at Mach 6 and Reynolds number of one half million per foot for 0 deg and -5 deg angle-of-attack. Selected thermocouples were chosen from the Orbiter and external tank to be used for obtaining heat transfer measurements. A maximum of 42 thermocouples could be measured by the facility data acquisition at one time and no attempt was made to record the excess thermocouples located on the model. Photographs of the test configurations are shown. |
| File Size | 40039941 |
| Page Count | 627 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760009060 |
| Archival Resource Key | ark:/13960/t16m81f9r |
| Language | English |
| Publisher Date | 1976-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Tables Data External Tanks Hypersonic Speed Scale Models Aerodynamic Heat Transfer Thermocouples Wind Tunnel Tests Hypersonic Heat Transfer Angle of Attack Space Shuttle Orbiters Boundary Layers 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 |
