Research Article
Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects
Table 2
Waypoints adopted for aerodynamic computation.
| Waypoint | Flow regime | Angle of attack | Altitude |
| 1 | Hypersonic | 44° | (km) | 2 | High supersonic | 19° | (km) | 3 | Low supersonic | 14° | (km) | 4 | Subsonic | 10° | (km) |
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