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 𝑅_𝑛=4.69m.

Apollo 4, entry angle: −12.0^∘, entry velocity: 22500 ft/s, nose radius: 4.69m
Altitude	Velocity	Flight path angle γ	Mach number	Reynolds number	Stagnation point pressure	Stagnation point heat
(ft)	(ft/sec)	(deg)			(lbf/ft^2)	transfer rate 𝑞̇conv (W/cm^2)
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