High-Fidelity Aerothermal Engineering Analysis for Planetary Probes Using DOTNET Framework and OLAP Cubes Database : Table 1

]>High-Fidelity Aerothermal Engineering Analysis for Planetary Probes Using DOTNET Framework and OLAP Cubes Database : Table 1

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