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Aeroheating characteristics for a two-stage-to-orbit concept during separation at mach 6
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Liechty, Derek S. |
| Copyright Year | 2005 |
| Description | An experimental study was conducted to determine the proximity aeroheating characteristics for a two-stage-to-orbit concept in close proximity in the NASA Langley 20-Inch Mach 6 Air Tunnel. A new hybrid discrete thin-film resistance gauge technique was evaluated in this study and used to measure experimental interference heating levels between the booster and the orbiter at a constant freestream Reynolds number of 8.25 x 10(exp 6)/m and a variety of separation and axial offset distances. It was found that, as the orbiter separates from the booster and the booster falls away, the windward centerline heating increased on the orbiter by as much as 13-times over the baseline, single model heating distribution, and on the booster by as much as 6-times. The aeroheating database developed can be used for computational fluid dynamic code validation. |
| File Size | 911442 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050182988 |
| Archival Resource Key | ark:/13960/t1qg3p540 |
| Language | English |
| Publisher Date | 2005-06-03 |
| Access Restriction | Open |
| Subject Keyword | Launch Vehicles And Launch Operations Thin Films Stage Separation Launch Vehicles Aerodynamic Heating Wind Tunnel Tests Aerodynamic Interference Hypersonic Wind Tunnels Aerothermodynamics Thermography Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
