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 γMach numberReynolds numberStagnation point pressure Stagnation point heat
(ft)(ft/sec)(deg)(lbf/ )transfer rate (W/ )

250000.0022513.6912.0023.8365486.3330.70391.30
249000.0022512.3212.0023.8068432.2032.16395.82
248000.0022510.9612.0123.7771501.9733.69400.44