Table 11 Flow conditions of data assimilation cases.

30P30N

Ma = 0.17, Re = 1.71 × 10⁶, α = 5.5°, T_∞ = 295.56 K

Delta wing

Ma = 0.4, Re = 3.0 × 10⁶, α = 20.5°, T_∞ = 288.15 K

S805/S809 airfoil

S809: Ma = 0.15, Re = 2.0 × 10⁶, T_∞ = 300 K,

α = 12.2° (DA₁)/14.2° (DA₂)

S805: Ma = 0.15, Re = 1.0 × 10⁶, T_∞ = 300 K

α = 12.2° (DA₃)/15.2° (DA₄)

M6 wing

Ma = 0.8395, Re = 1.172 × 10⁷, α = 6.06°, T_∞ = 288.15 K

NASA hump

Ma = 0.1, Re = 936,000, T_∞ = 298.33 K,

Inlet P₀/P_∞ = 1.007, Inlet T₀/T_∞ = 1.002, Outlet P/P_∞ = 0.99962