Table 7 Flow conditions for numerical simulation of civil aircraft.
From: High-Reynolds-Number Turbulence Database: AeroFlowData
Case | Flow conditions |
|---|---|
RAE2822 airfoil | Ma = 0.734, Re = 6.5 × 106, α = 2.79°, T∞ = 288.15 K |
S809 airfoil | Ma = 0.15, Re = 2 × 106, α = 10.2/12.2/14.2°, T∞ = 288.15 K |
30P30N airfoil | Ma = 0.17, Re = 1.7 × 106, α = 5.5°, T∞ = 295.56 K |
CRM wing body | Ma = 0.85, Re = 2 × 107/m, α = 2.5°, T∞ = 288.15 K |
HiLiftPW-3 | Ma = 0.172, Re = 1.93 × 106, α = 10.47°, T∞ = 289.44 K |
CHN-T1 | Ma = 0.6, Re = 3.565 × 106, α = 8°, T∞ = 298.15K Ma = 0.7, Re = 3.565 × 106, α = 5°, T∞ = 298.15K Ma = 0.7, Re = 6.48 × 106, α = 6°, T∞ = 298.15K Ma = 0.85, Re = 3.565 × 106, α = 8°, T∞ = 298.15 K |
M6 wing | Ma = 0.8395, Re = 1.172 × 107, α = 3.06°, T∞ = 288.15 K |
Delta wing | Ma = 0.4, Re = 3 × 106, α = 20.5°, T∞ = 288.15 K |
