XFOIL Version 6.96 Calculated polar for: WB-135/35 13.5% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.3807 0.10443 0.09747 -0.0514 1.0000 0.0470 -11.000 -0.3892 0.09900 0.09214 -0.0532 1.0000 0.0469 -10.750 -0.4007 0.09315 0.08639 -0.0551 1.0000 0.0467 -10.500 -0.4173 0.08668 0.08003 -0.0575 1.0000 0.0463 -10.250 -0.4387 0.07993 0.07341 -0.0603 1.0000 0.0457 -10.000 -0.4656 0.07309 0.06663 -0.0632 1.0000 0.0450 -9.750 -0.4951 0.06716 0.06072 -0.0656 1.0000 0.0443 -9.500 -0.5276 0.06271 0.05629 -0.0665 1.0000 0.0437 -9.250 -0.5599 0.05972 0.05331 -0.0647 1.0000 0.0431 -9.000 -0.5859 0.05683 0.05034 -0.0625 1.0000 0.0429 -8.750 -0.6054 0.05416 0.04752 -0.0601 1.0000 0.0428 -8.500 -0.6192 0.05155 0.04472 -0.0577 1.0000 0.0430 -8.250 -0.6276 0.04901 0.04194 -0.0555 1.0000 0.0436 -8.000 -0.6087 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0.01534 -0.0811 0.7278 1.0000 1.750 0.5026 0.02626 0.01543 -0.0802 0.7177 1.0000 2.000 0.5369 0.02608 0.01515 -0.0807 0.7101 1.0000 2.250 0.5557 0.02638 0.01541 -0.0791 0.6983 1.0000 2.500 0.5795 0.02650 0.01548 -0.0782 0.6875 1.0000 2.750 0.6144 0.02623 0.01515 -0.0787 0.6792 1.0000 3.000 0.6336 0.02648 0.01540 -0.0770 0.6664 1.0000 3.250 0.6549 0.02664 0.01555 -0.0757 0.6536 1.0000 3.500 0.6780 0.02673 0.01563 -0.0745 0.6408 1.0000 3.750 0.7020 0.02677 0.01569 -0.0734 0.6278 1.0000 4.000 0.7261 0.02680 0.01572 -0.0723 0.6142 1.0000 4.250 0.7490 0.02686 0.01579 -0.0711 0.5997 1.0000 4.500 0.7706 0.02696 0.01593 -0.0697 0.5842 1.0000 4.750 0.7919 0.02711 0.01610 -0.0682 0.5683 1.0000 5.000 0.8132 0.02727 0.01628 -0.0668 0.5519 1.0000 5.250 0.8351 0.02745 0.01648 -0.0655 0.5356 1.0000 5.500 0.8574 0.02764 0.01669 -0.0643 0.5196 1.0000 5.750 0.8800 0.02788 0.01693 -0.0632 0.5042 1.0000 6.000 0.9026 0.02817 0.01722 -0.0621 0.4896 1.0000 6.250 0.9251 0.02853 0.01760 -0.0610 0.4756 1.0000 6.500 0.9476 0.02895 0.01801 -0.0600 0.4626 1.0000 6.750 0.9709 0.02939 0.01846 -0.0592 0.4507 1.0000 7.000 0.9962 0.02979 0.01885 -0.0586 0.4396 1.0000 7.250 1.0159 0.03047 0.01965 -0.0575 0.4284 1.0000 7.500 1.0362 0.03118 0.02044 -0.0564 0.4181 1.0000 7.750 1.0616 0.03174 0.02102 -0.0560 0.4087 1.0000 8.000 1.0808 0.03256 0.02198 -0.0549 0.3994 1.0000 8.250 1.1023 0.03336 0.02291 -0.0541 0.3910 1.0000 8.500 1.1257 0.03410 0.02380 -0.0535 0.3827 1.0000 8.750 1.1389 0.03503 0.02487 -0.0516 0.3720 1.0000 9.000 1.1512 0.03575 0.02565 -0.0494 0.3591 1.0000 9.250 1.1605 0.03646 0.02640 -0.0468 0.3459 1.0000 9.500 1.1700 0.03719 0.02717 -0.0442 0.3333 1.0000 9.750 1.1757 0.03798 0.02798 -0.0414 0.3201 1.0000 10.000 1.1726 0.03924 0.02941 -0.0380 0.3080 1.0000 10.250 1.1746 0.04055 0.03089 -0.0354 0.2978 1.0000 10.500 1.1794 0.04169 0.03215 -0.0331 0.2874 1.0000 10.750 1.1797 0.04306 0.03365 -0.0308 0.2761 1.0000 11.000 1.1734 0.04503 0.03587 -0.0284 0.2642 1.0000 11.250 1.1693 0.04707 0.03811 -0.0266 0.2524 1.0000 11.500 1.1620 0.04944 0.04065 -0.0249 0.2379 1.0000 11.750 1.1522 0.05225 0.04360 -0.0237 0.2197 1.0000 12.000 1.1399 0.05568 0.04718 -0.0231 0.1960 1.0000 12.250 1.1294 0.05922 0.05071 -0.0228 0.1660 1.0000 12.500 1.1174 0.06310 0.05439 -0.0226 0.1275 1.0000 12.750 1.0965 0.06838 0.05925 -0.0231 0.0871 1.0000 13.250 1.0609 0.07979 0.07051 -0.0254 0.0641 1.0000 13.500 1.0460 0.08559 0.07636 -0.0270 0.0592 1.0000 13.750 1.0333 0.09125 0.08210 -0.0287 0.0552 1.0000 14.000 1.0209 0.09701 0.08794 -0.0306 0.0521 1.0000 14.250 1.0107 0.10248 0.09347 -0.0324 0.0500 1.0000