High-Fidelity Aerothermal Engineering Analysis for Planetary Probes Using DOTNET Framework and OLAP Cubes Database

Table 2

OLAP driven trajectory analysis for Apollo 4 at an entry velocity of 36545 ft/s and 𝑅_𝑛=5.69m.

Apollo 4, entry angle: −6.93^∘, entry velocity: 36545ft/s, nose radius: 5.69m
Altitude	Velocity	Flight path angle	Mach	Reynolds	Stagnation point pressure	Stagnation point heat
(ft)	(ft/sec)	γ (deg)	number	number	(lbf/ft^2)	transfer rate 𝑞̇conv (W/cm^2)
250000.00	36545.00	6.93	33.75	106364.35	81.02	482.53
249000.00	36544.30	6.92	33.75	111144.56	84.87	482.90
248000.00	36544.00	6.91	33.70	116125.59	88.89	483.01