Hypersonic Aerothermo ·
Bow Shock + Boundary Layer
un
seel
.com · Mach 5+ · T_stag ≈ 56·M² K
Mach
0.0
T_stag
220
K
State
—
Freestream (220 K)
Bow shock
Stagnation (hot)
Carbon-carbon nose
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seel
.com · Hypersonic Aerothermo