XFOIL Version 6.96 Calculated polar for: E195 (11.82%) 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3861 0.09211 0.08715 -0.0429 1.0000 0.0303 -9.500 -0.3902 0.08749 0.08261 -0.0448 1.0000 0.0297 -9.250 -0.3978 0.08233 0.07753 -0.0471 1.0000 0.0291 -8.750 -0.4790 0.06052 0.05582 -0.0613 1.0000 0.0263 -8.500 -0.5014 0.05664 0.05182 -0.0607 1.0000 0.0261 -8.250 -0.5168 0.05385 0.04896 -0.0585 1.0000 0.0260 -8.000 -0.5084 0.04832 0.04307 -0.0628 0.9877 0.0258 -7.750 -0.4911 0.04301 0.03723 -0.0670 0.9739 0.0258 -7.500 -0.4706 0.03857 0.03222 -0.0697 0.9608 0.0259 -7.250 -0.4470 0.03493 0.02800 -0.0715 0.9485 0.0260 -7.000 -0.4214 0.03187 0.02452 -0.0729 0.9367 0.0263 -6.750 -0.3930 0.02964 0.02205 -0.0743 0.9262 0.0273 -6.500 -0.3638 0.02805 0.02019 -0.0754 0.9151 0.0289 -6.250 -0.3353 0.02644 0.01829 -0.0761 0.9032 0.0306 -6.000 -0.3063 0.02475 0.01628 -0.0765 0.8921 0.0316 -5.750 -0.2768 0.02326 0.01454 -0.0768 0.8818 0.0326 -5.500 -0.2487 0.02205 0.01310 -0.0769 0.8709 0.0338 -5.250 -0.2237 0.02088 0.01185 -0.0766 0.8592 0.0355 -5.000 -0.1979 0.02003 0.01089 -0.0763 0.8482 0.0380 -4.750 -0.1711 0.01931 0.00998 -0.0760 0.8385 0.0430 -4.500 -0.1463 0.01854 0.00916 -0.0756 0.8279 0.0511 -4.250 -0.1215 0.01774 0.00830 -0.0750 0.8178 0.0674 -4.000 -0.0960 0.01700 0.00767 -0.0747 0.8094 0.1031 -3.750 -0.0719 0.01635 0.00730 -0.0744 0.7997 0.1679 -3.500 -0.0479 0.01571 0.00701 -0.0740 0.7912 0.2522 -3.250 -0.0230 0.01526 0.00673 -0.0736 0.7831 0.3227 -3.000 0.0014 0.01494 0.00658 -0.0730 0.7749 0.3950 -2.750 0.0267 0.01469 0.00643 -0.0723 0.7676 0.4628 -2.500 0.0514 0.01450 0.00633 -0.0715 0.7598 0.5199 -2.250 0.0770 0.01433 0.00620 -0.0708 0.7531 0.5713 -2.000 0.1021 0.01420 0.00613 -0.0700 0.7458 0.6207 -1.750 0.1275 0.01407 0.00606 -0.0691 0.7393 0.6706 -1.500 0.1527 0.01397 0.00601 -0.0681 0.7328 0.7211 -1.250 0.1786 0.01388 0.00599 -0.0672 0.7262 0.7744 -1.000 0.2091 0.01382 0.00594 -0.0670 0.7208 0.8307 -0.750 0.2472 0.01382 0.00593 -0.0686 0.7139 0.8857 -0.500 0.2923 0.01383 0.00582 -0.0718 0.7085 0.9316 -0.250 0.3368 0.01389 0.00576 -0.0753 0.7022 0.9686 0.000 0.3848 0.01390 0.00564 -0.0796 0.6961 0.9956 0.250 0.4120 0.01400 0.00560 -0.0798 0.6907 1.0000 0.500 0.4339 0.01415 0.00568 -0.0790 0.6841 1.0000 0.750 0.4577 0.01428 0.00570 -0.0783 0.6789 1.0000 1.000 0.4804 0.01446 0.00582 -0.0775 0.6727 1.0000 1.250 0.5039 0.01463 0.00592 -0.0768 0.6669 1.0000 1.500 0.5287 0.01479 0.00600 -0.0762 0.6621 1.0000 1.750 0.5515 0.01501 0.00621 -0.0755 0.6555 1.0000 2.000 0.5763 0.01518 0.00633 -0.0749 0.6504 1.0000 2.250 0.6005 0.01539 0.00654 -0.0743 0.6448 1.0000 2.500 0.6245 0.01561 0.00676 -0.0737 0.6387 1.0000 2.750 0.6504 0.01578 0.00689 -0.0733 0.6340 1.0000 3.250 0.6987 0.01625 0.00743 -0.0721 0.6218 1.0000 3.500 0.7237 0.01647 0.00767 -0.0716 0.6163 1.0000 3.750 0.7475 0.01673 0.00798 -0.0710 0.6095 1.0000 4.000 0.7740 0.01688 0.00815 -0.0707 0.6044 1.0000 4.250 0.7966 0.01718 0.00855 -0.0699 0.5964 1.0000 4.500 0.8228 0.01732 0.00871 -0.0694 0.5903 1.0000 4.750 0.8454 0.01758 0.00908 -0.0686 0.5816 1.0000 5.000 0.8717 0.01768 0.00922 -0.0681 0.5746 1.0000 5.250 0.8939 0.01792 0.00958 -0.0672 0.5645 1.0000 5.500 0.9177 0.01808 0.00983 -0.0664 0.5551 1.0000 5.750 0.9430 0.01814 0.00994 -0.0657 0.5458 1.0000 6.000 0.9649 0.01833 0.01028 -0.0646 0.5338 1.0000 6.250 0.9871 0.01849 0.01056 -0.0636 0.5214 1.0000 6.500 1.0093 0.01863 0.01081 -0.0624 0.5078 1.0000 6.750 1.0310 0.01877 0.01106 -0.0613 0.4928 1.0000 7.000 1.0523 0.01892 0.01131 -0.0600 0.4759 1.0000 7.250 1.0723 0.01913 0.01162 -0.0585 0.4565 1.0000 7.500 1.0909 0.01939 0.01196 -0.0569 0.4337 1.0000 7.750 1.1078 0.01973 0.01233 -0.0550 0.4054 1.0000 8.000 1.1222 0.02021 0.01276 -0.0528 0.3699 1.0000 8.250 1.1330 0.02091 0.01332 -0.0501 0.3279 1.0000 8.500 1.1391 0.02191 0.01412 -0.0470 0.2833 1.0000 8.750 1.1402 0.02319 0.01515 -0.0435 0.2394 1.0000 9.000 1.1364 0.02462 0.01633 -0.0394 0.2003 1.0000 9.250 1.1330 0.02621 0.01769 -0.0358 0.1654 1.0000 9.750 1.1282 0.02979 0.02087 -0.0302 0.1073 1.0000 10.000 1.1279 0.03168 0.02263 -0.0282 0.0841 1.0000 10.250 1.1297 0.03355 0.02446 -0.0264 0.0690 1.0000 10.500 1.1309 0.03558 0.02649 -0.0249 0.0550 1.0000 10.750 1.1304 0.03787 0.02876 -0.0234 0.0434 1.0000 11.000 1.1291 0.04036 0.03125 -0.0221 0.0360 1.0000 11.250 1.1294 0.04277 0.03373 -0.0211 0.0308 1.0000 11.500 1.1284 0.04541 0.03642 -0.0202 0.0279 1.0000 11.750 1.1300 0.04785 0.03901 -0.0194 0.0254 1.0000 12.000 1.1305 0.05046 0.04173 -0.0189 0.0238 1.0000 12.250 1.1298 0.05328 0.04465 -0.0184 0.0227 1.0000 12.500 1.1270 0.05639 0.04783 -0.0180 0.0217 1.0000 12.750 1.1287 0.05907 0.05068 -0.0177 0.0211 1.0000 13.000 1.1306 0.06181 0.05358 -0.0173 0.0204 1.0000 13.250 1.1327 0.06459 0.05650 -0.0170 0.0197 1.0000 13.500 1.1349 0.06743 0.05949 -0.0168 0.0190 1.0000 13.750 1.1380 0.07024 0.06247 -0.0167 0.0186 1.0000 14.000 1.1399 0.07326 0.06563 -0.0167 0.0181 1.0000 14.250 1.1404 0.07650 0.06898 -0.0171 0.0175 1.0000 14.500 1.1415 0.07979 0.07238 -0.0175 0.0172 1.0000 14.750 1.1409 0.08331 0.07599 -0.0181 0.0167 1.0000 15.000 1.1396 0.08719 0.08007 -0.0188 0.0164 1.0000 15.250 1.1343 0.09184 0.08500 -0.0202 0.0159 1.0000 15.500 1.1289 0.09662 0.09001 -0.0218 0.0156 1.0000 15.750 1.1219 0.10175 0.09536 -0.0238 0.0154 1.0000 16.000 1.1128 0.10748 0.10132 -0.0263 0.0153 1.0000 16.250 1.1018 0.11378 0.10785 -0.0294 0.0153 1.0000 16.500 1.0889 0.12074 0.11503 -0.0331 0.0152 1.0000 16.750 1.0742 0.12842 0.12292 -0.0374 0.0153 1.0000 17.000 1.0575 0.13704 0.13175 -0.0426 0.0153 1.0000 17.250 1.0401 0.14642 0.14130 -0.0485 0.0156 1.0000 17.500 1.0193 0.15754 0.15257 -0.0554 0.0158 1.0000