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Implicit weighted essentially nonoscillatory schemes for the compressible Navier-Stokes equations

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Fig. 1 O-type grid 241 ££ 45 for NACA 0012 airfoil.
Fig. 7 RAE 2822 airfoil surface pressure distribution at M 1 = 0:731;
Table 1 Lift and drag coefŽ cients for RAE 2822 airfoil at M 1 = 0:725; ® = 2:92 deg, and Re c = 6:5 ££ 10 6
Fig. 13 Steady pressure distributions for ONERA M6 wing at M 1 = 0:8395; ® = 3:06 deg, and Re c = 2:6 ££ 10 6 .
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