132 A. A. HASSAN AND L. N. SANKAR J. AIRCRAFT
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1 VOL.
2 132 A. A. HASSAN AND L. N. SANKAR J. AIRCRAFT separation
3 JAN.-FEB SEPARATION CONTROL 133 H Fig. 1 Physical domain of interest in the present flowfield simulations.
4 134 A. A. HASSAN AND L. N. SANKAR J. AIRCRAFT
5 JAN.-FEB SEPARATION CONTROL 135 Experimental Facility The smoke wire flow visualization experiments were performed
6 136
7 JAN.-FEB SEPARATION CONTROL 137 p=0.18 d- Fig. 8 Predicted near-field velocity vector plots for the flow past the modified NACA 0012 airfoil (Eminf = 0.50, Re = 8 X lo4, a = 10 deg, laminar). pzo.0 p=0.20 pz0.25 Fig. 9 Predicted near-field velocity vector plots for the flow past the modified NACA 0012 airfoil (Eminf = 0.50, Re = 8 x lo4, a = 15 deg, laminar). _- Fig. 10 Predicted near-field velocity vector plots for the flow past the modified NACA 0012 airfoil (Eminf = 0.50, Re = 8 X lo4, a = 20 deg, laminar).
8 138
9 JAN.-FEB SEPARATION CONTROL 139 NACA airfoil having leading-edge rotation
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