XFOIL Version 6.96 Calculated polar for: CLARK-Y 11.7% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.3683 0.10567 0.10330 -0.0408 1.0000 0.0293 -10.500 -0.6823 0.04568 0.04313 -0.0696 0.9978 0.0189 -10.250 -0.6978 0.03453 0.03111 -0.0784 0.9877 0.0191 -10.000 -0.6810 0.03037 0.02639 -0.0811 0.9839 0.0194 -9.750 -0.6692 0.02674 0.02230 -0.0813 0.9776 0.0198 -9.500 -0.6439 0.02477 0.02018 -0.0825 0.9743 0.0203 -9.250 -0.6129 0.02362 0.01892 -0.0842 0.9723 0.0209 -9.000 -0.5809 0.02233 0.01745 -0.0859 0.9708 0.0216 -8.750 -0.5598 0.02133 0.01629 -0.0852 0.9643 0.0223 -8.500 -0.5290 0.02029 0.01503 -0.0863 0.9615 0.0232 -8.250 -0.4985 0.01871 0.01323 -0.0876 0.9595 0.0242 -8.000 -0.4640 0.01788 0.01238 -0.0894 0.9582 0.0253 -7.750 -0.4280 0.01708 0.01148 -0.0914 0.9570 0.0264 -7.500 -0.4049 0.01642 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-0.0998 0.6126 1.0000 2.250 0.7313 0.00747 0.00254 -0.0983 0.5977 1.0000 2.500 0.7518 0.00759 0.00259 -0.0967 0.5819 1.0000 2.750 0.7721 0.00772 0.00266 -0.0951 0.5658 1.0000 3.000 0.7925 0.00787 0.00273 -0.0935 0.5495 1.0000 3.250 0.8128 0.00803 0.00282 -0.0919 0.5324 1.0000 3.500 0.8328 0.00820 0.00293 -0.0903 0.5144 1.0000 3.750 0.8524 0.00840 0.00305 -0.0886 0.4951 1.0000 4.000 0.8713 0.00863 0.00319 -0.0867 0.4748 1.0000 4.250 0.8897 0.00889 0.00334 -0.0848 0.4520 1.0000 4.500 0.9077 0.00917 0.00350 -0.0828 0.4284 1.0000 4.750 0.9260 0.00946 0.00369 -0.0809 0.4083 1.0000 5.000 0.9448 0.00973 0.00388 -0.0791 0.3887 1.0000 5.250 0.9638 0.01000 0.00408 -0.0773 0.3727 1.0000 5.500 0.9830 0.01027 0.00429 -0.0756 0.3586 1.0000 5.750 1.0020 0.01055 0.00451 -0.0739 0.3452 1.0000 6.000 1.0210 0.01083 0.00473 -0.0722 0.3325 1.0000 6.250 1.0408 0.01107 0.00495 -0.0706 0.3206 1.0000 6.500 1.0604 0.01133 0.00519 -0.0690 0.3110 1.0000 6.750 1.0791 0.01162 0.00544 -0.0673 0.3018 1.0000 7.000 1.0992 0.01184 0.00568 -0.0658 0.2929 1.0000 7.250 1.1174 0.01214 0.00595 -0.0640 0.2837 1.0000 7.500 1.1368 0.01238 0.00620 -0.0625 0.2746 1.0000 7.750 1.1548 0.01266 0.00648 -0.0606 0.2658 1.0000 8.000 1.1704 0.01297 0.00676 -0.0583 0.2555 1.0000 8.250 1.1878 0.01322 0.00703 -0.0564 0.2446 1.0000 8.500 1.2037 0.01355 0.00734 -0.0542 0.2313 1.0000 8.750 1.2185 0.01395 0.00768 -0.0520 0.2142 1.0000 9.000 1.2308 0.01449 0.00811 -0.0494 0.1879 1.0000 9.250 1.2362 0.01542 0.00877 -0.0458 0.1453 1.0000 9.500 1.2406 0.01646 0.00960 -0.0423 0.1154 1.0000 9.750 1.2492 0.01733 0.01038 -0.0394 0.1014 1.0000 10.000 1.2610 0.01803 0.01108 -0.0371 0.0937 1.0000 10.250 1.2713 0.01884 0.01189 -0.0347 0.0877 1.0000 10.500 1.2847 0.01949 0.01259 -0.0328 0.0834 1.0000 10.750 1.2949 0.02035 0.01345 -0.0306 0.0793 1.0000 11.000 1.3043 0.02128 0.01442 -0.0284 0.0757 1.0000 11.250 1.3183 0.02196 0.01517 -0.0268 0.0728 1.0000 11.500 1.3295 0.02284 0.01608 -0.0251 0.0699 1.0000 11.750 1.3363 0.02404 0.01730 -0.0229 0.0668 1.0000 12.000 1.3450 0.02515 0.01847 -0.0211 0.0645 1.0000 12.250 1.3585 0.02596 0.01936 -0.0199 0.0622 1.0000 12.500 1.3697 0.02697 0.02042 -0.0185 0.0598 1.0000 12.750 1.3769 0.02830 0.02179 -0.0170 0.0577 1.0000 13.000 1.3772 0.03019 0.02372 -0.0150 0.0551 1.0000 13.250 1.3902 0.03118 0.02481 -0.0141 0.0536 1.0000 13.500 1.4006 0.03239 0.02610 -0.0131 0.0517 1.0000 13.750 1.4091 0.03379 0.02755 -0.0121 0.0497 1.0000 14.000 1.4126 0.03566 0.02946 -0.0110 0.0478 1.0000 14.250 1.4115 0.03802 0.03188 -0.0098 0.0460 1.0000 14.500 1.4214 0.03945 0.03341 -0.0093 0.0444 1.0000 14.750 1.4293 0.04111 0.03516 -0.0087 0.0426 1.0000 15.000 1.4340 0.04311 0.03721 -0.0082 0.0410 1.0000 15.250 1.4315 0.04593 0.04008 -0.0077 0.0392 1.0000 15.500 1.4327 0.04846 0.04271 -0.0074 0.0378 1.0000 15.750 1.4377 0.05065 0.04499 -0.0073 0.0362 1.0000 16.000 1.4404 0.05315 0.04757 -0.0073 0.0346 1.0000 16.250 1.4385 0.05626 0.05073 -0.0074 0.0333 1.0000 16.500 1.4283 0.06044 0.05497 -0.0078 0.0319 1.0000 16.750 1.4320 0.06302 0.05768 -0.0081 0.0306 1.0000 17.000 1.4316 0.06617 0.06094 -0.0087 0.0292 1.0000 17.250 1.4262 0.07004 0.06488 -0.0094 0.0283 1.0000 17.500 1.4185 0.07432 0.06922 -0.0104 0.0271 1.0000 17.750 1.4060 0.07926 0.07424 -0.0116 0.0263 1.0000 18.000 1.4032 0.08299 0.07810 -0.0126 0.0254 1.0000 18.250 1.3959 0.08739 0.08260 -0.0138 0.0247 1.0000 18.500 1.3895 0.09174 0.08705 -0.0152 0.0238 1.0000 18.750 1.3800 0.09657 0.09196 -0.0168 0.0231 1.0000 19.000 1.3682 0.10185 0.09729 -0.0187 0.0222 1.0000