XFOIL Version 6.96 Calculated polar for: AH 93-W-215 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0856 0.08056 0.07668 -0.0672 1.0000 0.0337 -19.500 -1.0923 0.07642 0.07246 -0.0691 1.0000 0.0339 -19.250 -1.1018 0.07202 0.06797 -0.0710 1.0000 0.0343 -19.000 -1.1162 0.06714 0.06302 -0.0730 1.0000 0.0348 -18.750 -1.1251 0.06303 0.05884 -0.0746 1.0000 0.0352 -18.500 -1.1318 0.05928 0.05503 -0.0759 1.0000 0.0355 -18.250 -1.1347 0.05609 0.05178 -0.0770 1.0000 0.0360 -18.000 -1.1379 0.05294 0.04857 -0.0779 1.0000 0.0365 -17.750 -1.1364 0.05038 0.04595 -0.0785 1.0000 0.0370 -17.500 -1.1362 0.04777 0.04328 -0.0790 1.0000 0.0374 -17.250 -1.1328 0.04556 0.04101 -0.0793 1.0000 0.0379 -17.000 -1.1293 0.04340 0.03878 -0.0795 1.0000 0.0383 -16.750 -1.1298 0.04094 0.03626 -0.0796 1.0000 0.0389 -16.500 -1.1320 0.03845 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0.00253 -0.0697 0.5605 0.4397 -2.250 0.0913 0.00804 0.00249 -0.0690 0.5581 0.4601 -2.000 0.1161 0.00798 0.00246 -0.0683 0.5555 0.4773 -1.750 0.1414 0.00796 0.00245 -0.0677 0.5524 0.4926 -1.500 0.1679 0.00796 0.00246 -0.0674 0.5495 0.5059 -1.250 0.1934 0.00791 0.00244 -0.0668 0.5477 0.5190 -1.000 0.2189 0.00786 0.00243 -0.0663 0.5454 0.5296 -0.750 0.2450 0.00783 0.00242 -0.0658 0.5429 0.5400 -0.500 0.2704 0.00780 0.00241 -0.0652 0.5404 0.5501 -0.250 0.2961 0.00780 0.00240 -0.0647 0.5375 0.5597 0.000 0.3215 0.00782 0.00241 -0.0641 0.5344 0.5680 0.250 0.3478 0.00786 0.00245 -0.0638 0.5313 0.5771 0.500 0.3736 0.00783 0.00245 -0.0633 0.5293 0.5855 0.750 0.3986 0.00780 0.00246 -0.0626 0.5268 0.5946 1.000 0.4245 0.00780 0.00247 -0.0621 0.5240 0.6034 1.250 0.4487 0.00778 0.00249 -0.0613 0.5210 0.6133 1.500 0.4734 0.00781 0.00251 -0.0606 0.5179 0.6233 1.750 0.4973 0.00785 0.00256 -0.0598 0.5141 0.6348 2.000 0.5225 0.00786 0.00259 -0.0591 0.5117 0.6443 2.250 0.5465 0.00783 0.00262 -0.0583 0.5090 0.6537 2.500 0.5709 0.00783 0.00265 -0.0575 0.5058 0.6623 2.750 0.5942 0.00784 0.00267 -0.0565 0.5025 0.6707 3.000 0.6154 0.00787 0.00271 -0.0551 0.4989 0.6798 3.250 0.6382 0.00794 0.00276 -0.0540 0.4951 0.6880 3.500 0.6601 0.00791 0.00281 -0.0527 0.4924 0.6979 3.750 0.6829 0.00792 0.00284 -0.0517 0.4889 0.7072 4.000 0.7042 0.00793 0.00290 -0.0503 0.4853 0.7173 4.250 0.7248 0.00800 0.00297 -0.0488 0.4812 0.7277 4.500 0.7457 0.00807 0.00307 -0.0473 0.4773 0.7381 4.750 0.7688 0.00810 0.00314 -0.0463 0.4738 0.7485 5.000 0.7904 0.00814 0.00323 -0.0450 0.4695 0.7591 5.250 0.8108 0.00823 0.00332 -0.0435 0.4651 0.7698 5.500 0.8288 0.00834 0.00345 -0.0416 0.4603 0.7810 5.750 0.8514 0.00840 0.00355 -0.0405 0.4567 0.7911 6.000 0.8719 0.00846 0.00367 -0.0390 0.4521 0.8018 6.500 0.9089 0.00870 0.00394 -0.0354 0.4418 0.8233 6.750 0.9305 0.00879 0.00406 -0.0342 0.4373 0.8332 7.000 0.9493 0.00891 0.00422 -0.0325 0.4316 0.8441 7.250 0.9650 0.00910 0.00440 -0.0302 0.4257 0.8547 7.500 0.9866 0.00919 0.00455 -0.0291 0.4212 0.8659 7.750 1.0063 0.00934 0.00473 -0.0277 0.4151 0.8766 8.250 1.0493 0.00969 0.00516 -0.0258 0.4036 0.9006 8.500 1.0764 0.00992 0.00540 -0.0262 0.3965 0.9123 8.750 1.1087 0.01019 0.00569 -0.0277 0.3893 0.9238 9.000 1.1518 0.01046 0.00599 -0.0316 0.3812 0.9326 9.250 1.1954 0.01084 0.00636 -0.0357 0.3723 0.9412 9.500 1.2426 0.01115 0.00669 -0.0404 0.3644 0.9482 9.750 1.2842 0.01157 0.00710 -0.0442 0.3558 0.9576 10.250 1.3480 0.01255 0.00807 -0.0477 0.3380 1.0000 10.500 1.3635 0.01303 0.00854 -0.0462 0.3300 1.0000 10.750 1.3752 0.01368 0.00916 -0.0443 0.3222 1.0000 11.000 1.3895 0.01428 0.00976 -0.0429 0.3141 1.0000 11.250 1.3983 0.01517 0.01062 -0.0409 0.3055 1.0000 11.500 1.4096 0.01602 0.01147 -0.0394 0.2967 1.0000 11.750 1.4172 0.01715 0.01259 -0.0378 0.2890 1.0000 12.000 1.4277 0.01821 0.01365 -0.0366 0.2810 1.0000 12.250 1.4326 0.01969 0.01512 -0.0351 0.2728 1.0000 12.500 1.4421 0.02095 0.01639 -0.0341 0.2654 1.0000 12.750 1.4443 0.02274 0.01817 -0.0327 0.2574 1.0000 13.000 1.4516 0.02421 0.01964 -0.0317 0.2495 1.0000 13.250 1.4514 0.02623 0.02165 -0.0303 0.2418 1.0000 13.500 1.4570 0.02785 0.02329 -0.0293 0.2340 1.0000 13.750 1.4538 0.03011 0.02553 -0.0279 0.2260 1.0000 14.000 1.4577 0.03187 0.02730 -0.0269 0.2180 1.0000 14.250 1.4547 0.03420 0.02961 -0.0256 0.2103 1.0000 14.500 1.4574 0.03614 0.03156 -0.0247 0.2034 1.0000 14.750 1.4535 0.03865 0.03405 -0.0236 0.1957 1.0000 15.000 1.4577 0.04054 0.03596 -0.0229 0.1890 1.0000 15.500 1.4562 0.04528 0.04068 -0.0214 0.1740 1.0000 15.750 1.4517 0.04807 0.04346 -0.0206 0.1668 1.0000 16.000 1.4545 0.05020 0.04560 -0.0201 0.1599 1.0000 16.250 1.4499 0.05309 0.04847 -0.0195 0.1532 1.0000 16.500 1.4519 0.05537 0.05075 -0.0192 0.1462 1.0000 16.750 1.4475 0.05834 0.05373 -0.0187 0.1401 1.0000 17.000 1.4503 0.06062 0.05601 -0.0185 0.1342 1.0000 17.250 1.4441 0.06383 0.05921 -0.0182 0.1269 1.0000 17.500 1.4460 0.06626 0.06165 -0.0180 0.1218 1.0000 17.750 1.4404 0.06952 0.06491 -0.0179 0.1158 1.0000 18.000 1.4423 0.07201 0.06742 -0.0179 0.1112 1.0000 18.500 1.4371 0.07806 0.07349 -0.0180 0.1011 1.0000 18.750 1.4310 0.08155 0.07698 -0.0182 0.0961 1.0000 19.000 1.4313 0.08433 0.07979 -0.0185 0.0919 1.0000 19.250 1.4253 0.08788 0.08334 -0.0188 0.0872 1.0000