Research Article
High-Fidelity Aerothermal Engineering Analysis for Planetary Probes Using DOTNET Framework and OLAP Cubes Database
Table 1
OLAP driven trajectory analysis for
Apollo 4 at an entry velocity of 22500 ft/s and
.
| Apollo 4, entry angle: , entry velocity: 22500 ft/s, nose radius: | Altitude | Velocity | Flight path angle γ | Mach number | Reynolds number | Stagnation point pressure | Stagnation point heat | (ft) | (ft/sec) | (deg) | | | (lbf/) | transfer rate (W/) |
| 250000.00 | 22513.69 | 12.00 | 23.83 | 65486.33 | 30.70 | 391.30 | 249000.00 | 22512.32 | 12.00 | 23.80 | 68432.20 | 32.16 | 395.82 | 248000.00 | 22510.96 | 12.01 | 23.77 | 71501.97 | 33.69 | 400.44 |
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