XFOIL Version 6.96 Calculated polar for: S9026 (9.5%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.7856 0.09862 0.09342 0.0009 1.0000 0.0346 -12.250 -0.8226 0.08518 0.07998 -0.0080 1.0000 0.0340 -12.000 -0.8550 0.07425 0.06897 -0.0162 1.0000 0.0332 -11.750 -0.8856 0.06547 0.06001 -0.0231 1.0000 0.0327 -11.500 -0.9112 0.05913 0.05346 -0.0271 1.0000 0.0323 -11.250 -0.9326 0.05445 0.04854 -0.0283 1.0000 0.0324 -11.000 -0.9502 0.05084 0.04467 -0.0273 1.0000 0.0327 -10.750 -0.9623 0.04761 0.04109 -0.0255 1.0000 0.0335 -10.500 -0.9668 0.04445 0.03750 -0.0239 1.0000 0.0344 -10.250 -0.9642 0.04145 0.03417 -0.0224 1.0000 0.0353 -10.000 -0.9544 0.03912 0.03171 -0.0213 1.0000 0.0363 -9.750 -0.9422 0.03715 0.02956 -0.0201 1.0000 0.0374 -9.500 -0.9284 0.03523 0.02740 -0.0190 1.0000 0.0389 -9.250 -0.9131 0.03349 0.02541 -0.0179 1.0000 0.0410 -9.000 -0.8964 0.03176 0.02335 -0.0167 1.0000 0.0435 -8.750 -0.8788 0.02994 0.02131 -0.0156 1.0000 0.0457 -8.500 -0.8603 0.02849 0.01981 -0.0147 1.0000 0.0479 -8.250 -0.8409 0.02718 0.01839 -0.0137 1.0000 0.0508 -8.000 -0.8205 0.02595 0.01692 -0.0126 1.0000 0.0547 -7.750 -0.8010 0.02476 0.01569 -0.0117 1.0000 0.0591 -7.500 -0.7803 0.02377 0.01462 -0.0107 1.0000 0.0644 -7.250 -0.7597 0.02270 0.01345 -0.0097 1.0000 0.0699 -7.000 -0.7385 0.02187 0.01258 -0.0088 1.0000 0.0774 -6.750 -0.7174 0.02101 0.01170 -0.0078 1.0000 0.0857 -6.500 -0.6955 0.02025 0.01085 -0.0069 1.0000 0.0957 -6.250 -0.6736 0.01955 0.01011 -0.0060 1.0000 0.1073 -6.000 -0.6519 0.01885 0.00943 -0.0051 1.0000 0.1206 -5.750 -0.6299 0.01819 0.00879 -0.0041 1.0000 0.1355 -5.500 -0.6080 0.01755 0.00819 -0.0032 1.0000 0.1515 -5.250 -0.5861 0.01696 0.00766 -0.0023 1.0000 0.1709 -5.000 -0.5638 0.01643 0.00717 -0.0013 1.0000 0.1926 -4.750 -0.5418 0.01590 0.00673 -0.0003 1.0000 0.2164 -4.500 -0.5198 0.01541 0.00634 0.0007 1.0000 0.2440 -4.250 -0.4979 0.01495 0.00597 0.0017 1.0000 0.2748 -4.000 -0.4760 0.01453 0.00567 0.0028 1.0000 0.3084 -3.750 -0.4544 0.01411 0.00540 0.0039 1.0000 0.3440 -3.500 -0.4326 0.01374 0.00516 0.0050 1.0000 0.3809 -3.250 -0.4111 0.01339 0.00494 0.0062 1.0000 0.4185 -3.000 -0.3897 0.01307 0.00478 0.0075 1.0000 0.4575 -2.750 -0.3684 0.01278 0.00465 0.0088 1.0000 0.4978 -2.500 -0.3474 0.01252 0.00456 0.0102 1.0000 0.5391 -2.250 -0.3267 0.01230 0.00450 0.0117 1.0000 0.5817 -2.000 -0.3060 0.01212 0.00448 0.0132 1.0000 0.6238 -1.750 -0.2853 0.01198 0.00450 0.0148 1.0000 0.6651 -1.500 -0.2546 0.01191 0.00456 0.0143 0.9942 0.7086 -1.250 -0.2142 0.01188 0.00466 0.0121 0.9824 0.7525 -1.000 -0.1744 0.01186 0.00474 0.0102 0.9697 0.7932 -0.750 -0.1336 0.01185 0.00481 0.0082 0.9567 0.8287 -0.500 -0.0913 0.01185 0.00486 0.0059 0.9427 0.8595 -0.250 -0.0462 0.01185 0.00490 0.0031 0.9270 0.8858 0.000 0.0000 0.01186 0.00491 0.0000 0.9081 0.9081 0.250 0.0462 0.01185 0.00490 -0.0030 0.8858 0.9270 0.500 0.0913 0.01185 0.00486 -0.0059 0.8595 0.9427 0.750 0.1336 0.01185 0.00481 -0.0082 0.8287 0.9566 1.000 0.1743 0.01186 0.00474 -0.0102 0.7930 0.9696 1.250 0.2142 0.01188 0.00466 -0.0121 0.7524 0.9824 1.500 0.2545 0.01191 0.00456 -0.0143 0.7084 0.9941 1.750 0.2854 0.01198 0.00450 -0.0148 0.6650 1.0000 2.000 0.3061 0.01211 0.00448 -0.0132 0.6241 1.0000 2.250 0.3268 0.01230 0.00450 -0.0117 0.5817 1.0000 2.500 0.3476 0.01252 0.00456 -0.0102 0.5394 1.0000 2.750 0.3686 0.01278 0.00465 -0.0088 0.4980 1.0000 3.000 0.3898 0.01307 0.00478 -0.0075 0.4574 1.0000 3.250 0.4113 0.01339 0.00495 -0.0062 0.4186 1.0000 3.500 0.4328 0.01374 0.00516 -0.0050 0.3808 1.0000 3.750 0.4545 0.01411 0.00540 -0.0039 0.3440 1.0000 4.250 0.4980 0.01495 0.00597 -0.0017 0.2747 1.0000 4.500 0.5199 0.01541 0.00634 -0.0007 0.2439 1.0000 4.750 0.5419 0.01590 0.00673 0.0003 0.2163 1.0000 5.000 0.5638 0.01643 0.00717 0.0013 0.1926 1.0000 5.250 0.5862 0.01696 0.00766 0.0022 0.1709 1.0000 5.500 0.6081 0.01755 0.00819 0.0032 0.1515 1.0000 5.750 0.6299 0.01819 0.00879 0.0041 0.1355 1.0000 6.000 0.6519 0.01885 0.00943 0.0051 0.1206 1.0000 6.250 0.6736 0.01955 0.01011 0.0060 0.1074 1.0000 6.500 0.6955 0.02026 0.01085 0.0069 0.0958 1.0000 6.750 0.7174 0.02101 0.01169 0.0078 0.0856 1.0000 7.000 0.7385 0.02186 0.01257 0.0088 0.0774 1.0000 7.250 0.7596 0.02270 0.01345 0.0097 0.0698 1.0000 7.500 0.7802 0.02377 0.01462 0.0107 0.0644 1.0000 7.750 0.8009 0.02476 0.01569 0.0117 0.0591 1.0000 8.000 0.8204 0.02594 0.01691 0.0127 0.0546 1.0000 8.250 0.8408 0.02718 0.01838 0.0137 0.0507 1.0000 8.500 0.8602 0.02849 0.01981 0.0147 0.0479 1.0000 8.750 0.8786 0.02994 0.02132 0.0157 0.0457 1.0000 9.000 0.8962 0.03175 0.02333 0.0167 0.0436 1.0000 9.250 0.9129 0.03348 0.02540 0.0179 0.0410 1.0000 9.500 0.9282 0.03522 0.02739 0.0190 0.0388 1.0000 9.750 0.9420 0.03713 0.02952 0.0202 0.0374 1.0000 10.000 0.9542 0.03913 0.03172 0.0213 0.0363 1.0000 10.250 0.9640 0.04146 0.03418 0.0224 0.0353 1.0000 10.500 0.9668 0.04444 0.03748 0.0239 0.0344 1.0000 10.750 0.9624 0.04759 0.04107 0.0255 0.0335 1.0000 11.000 0.9504 0.05087 0.04469 0.0273 0.0329 1.0000 11.250 0.9326 0.05452 0.04861 0.0283 0.0325 1.0000 11.500 0.9110 0.05916 0.05349 0.0271 0.0323 1.0000 11.750 0.8855 0.06548 0.06002 0.0230 0.0325 1.0000 12.000 0.8554 0.07423 0.06895 0.0162 0.0332 1.0000 12.250 0.8202 0.08589 0.08070 0.0073 0.0340 1.0000