Case 4

Geometry: CAE-AVM-DZ (deformed wing geometry, with support)

Flow conditions: M=0.85, Re=4.7 million, AOA=( -1.99, -0.01, 2.25, 2.45, 2.79, 3.00, 4.00, 5.50, 6.50, 8.02) deg, T₀=303.15 K

Parameters to be computed:

1. Cp distribution at six spanwise stations of the wing:
        -  η=20% (y=0.1372m, local chord=236.49mm)
        -  η=35% (y=0.2401m, local chord=183.45mm)
        -  η=45% (y=0.3087m, local chord=157.91mm)
        -  η=55% (y=0.3773m, local chord=137.88mm)
        -  η=65% (y=0.4459m, local chord=121.06mm)
        -  η=75% (y=0.5145m, local chord=104.29mm)
2. CL, CD, Cm