XFOIL Version 6.96 Calculated polar for: WORTMANN FX 75-193 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 ------ -------- --------- --------- -------- -------- -------- -15.000 -0.2951 0.06903 0.06499 -0.1628 0.8173 0.0142 -14.750 -0.3067 0.06397 0.05976 -0.1666 0.8169 0.0140 -14.500 -0.3286 0.05830 0.05392 -0.1697 0.8165 0.0140 -14.250 -0.3378 0.05415 0.04971 -0.1709 0.8160 0.0137 -14.000 -0.3521 0.05021 0.04562 -0.1721 0.8154 0.0136 -13.750 -0.3662 0.04665 0.04189 -0.1725 0.8146 0.0136 -13.500 -0.3770 0.04347 0.03857 -0.1723 0.8137 0.0133 -13.250 -0.3855 0.04087 0.03578 -0.1716 0.8125 0.0133 -13.000 -0.3927 0.03841 0.03313 -0.1706 0.8116 0.0134 -12.750 -0.3956 0.03630 0.03084 -0.1693 0.8106 0.0134 -12.500 -0.3943 0.03454 0.02892 -0.1681 0.8096 0.0134 -12.250 -0.3907 0.03313 0.02735 -0.1668 0.8086 0.0135 -12.000 -0.3831 0.03166 0.02574 -0.1656 0.8077 0.0135 -11.750 -0.3727 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0.00897 -0.1269 0.7085 0.7128 2.750 0.8290 0.01365 0.00879 -0.1275 0.7065 0.7140 3.000 0.8469 0.01370 0.00893 -0.1258 0.7016 0.7154 3.250 0.8743 0.01354 0.00880 -0.1259 0.6985 0.7168 3.500 0.9050 0.01331 0.00856 -0.1267 0.6957 0.7183 3.750 0.9374 0.01307 0.00830 -0.1278 0.6931 0.7200 4.000 0.9605 0.01303 0.00831 -0.1272 0.6884 0.7220 4.250 0.9843 0.01298 0.00828 -0.1268 0.6831 0.7243 4.500 1.0141 0.01288 0.00816 -0.1275 0.6792 0.7265 4.750 1.0441 0.01275 0.00802 -0.1283 0.6746 0.7282 5.000 1.0588 0.01262 0.00796 -0.1259 0.6661 0.7297 5.250 1.0828 0.01243 0.00776 -0.1252 0.6577 0.7311 5.500 1.0988 0.01239 0.00775 -0.1230 0.6479 0.7325 5.750 1.1178 0.01239 0.00776 -0.1215 0.6395 0.7339 6.000 1.1331 0.01239 0.00774 -0.1192 0.6297 0.7352 6.250 1.1430 0.01248 0.00784 -0.1160 0.6197 0.7366 6.500 1.1559 0.01261 0.00791 -0.1133 0.6077 0.7382 6.750 1.1614 0.01290 0.00817 -0.1094 0.5938 0.7400 7.000 1.1608 0.01336 0.00861 -0.1045 0.5782 0.7416 7.250 1.1604 0.01393 0.00914 -0.1000 0.5627 0.7428 7.500 1.1581 0.01467 0.00983 -0.0955 0.5456 0.7438 7.750 1.1593 0.01547 0.01058 -0.0918 0.5301 0.7446 8.000 1.1603 0.01633 0.01138 -0.0882 0.5135 0.7453 8.250 1.1614 0.01714 0.01213 -0.0847 0.4969 0.7462 8.500 1.1630 0.01798 0.01293 -0.0813 0.4799 0.7471 8.750 1.1627 0.01896 0.01385 -0.0777 0.4607 0.7482 9.000 1.1595 0.02011 0.01490 -0.0738 0.4376 0.7491 9.250 1.1548 0.02139 0.01606 -0.0698 0.4114 0.7498 9.500 1.1451 0.02297 0.01748 -0.0654 0.3785 0.7503 9.750 1.1406 0.02444 0.01880 -0.0618 0.3501 0.7507 10.000 1.1359 0.02604 0.02025 -0.0584 0.3196 0.7512 10.250 1.1306 0.02778 0.02182 -0.0550 0.2850 0.7518 10.500 1.1245 0.02969 0.02352 -0.0518 0.2493 0.7525 10.750 1.1161 0.03186 0.02545 -0.0486 0.2065 0.7530 11.000 1.1119 0.03389 0.02727 -0.0460 0.1682 0.7534 11.250 1.1029 0.03635 0.02946 -0.0432 0.1227 0.7536 11.500 1.0964 0.03878 0.03165 -0.0407 0.0846 0.7539 11.750 1.0971 0.04076 0.03350 -0.0391 0.0624 0.7544 12.000 1.0952 0.04304 0.03562 -0.0373 0.0395 0.7548 12.250 1.0971 0.04511 0.03761 -0.0359 0.0244 0.7551 12.500 1.1002 0.04716 0.03964 -0.0347 0.0192 0.7552 12.750 1.1080 0.04883 0.04137 -0.0339 0.0176 0.7554 13.000 1.1158 0.05056 0.04314 -0.0332 0.0165 0.7555 13.250 1.1214 0.05253 0.04515 -0.0325 0.0158 0.7558 13.500 1.1299 0.05427 0.04696 -0.0319 0.0152 0.7563 13.750 1.1370 0.05619 0.04894 -0.0314 0.0147 0.7565 14.000 1.1442 0.05812 0.05094 -0.0309 0.0144 0.7566 14.250 1.1501 0.06025 0.05313 -0.0305 0.0140 0.7567 14.500 1.1558 0.06243 0.05536 -0.0302 0.0137 0.7568 14.750 1.1609 0.06474 0.05774 -0.0300 0.0136 0.7569 15.000 1.1639 0.06730 0.06035 -0.0297 0.0133 0.7570 15.250 1.1664 0.06999 0.06311 -0.0296 0.0132 0.7571 15.500 1.1681 0.07282 0.06600 -0.0295 0.0131 0.7571 15.750 1.1710 0.07557 0.06882 -0.0296 0.0130 0.7572 16.000 1.1760 0.07810 0.07142 -0.0297 0.0129 0.7573 16.250 1.1804 0.08073 0.07412 -0.0299 0.0129 0.7575 16.500 1.1850 0.08336 0.07682 -0.0302 0.0128 0.7576 16.750 1.1904 0.08590 0.07942 -0.0304 0.0127 0.7577 17.000 1.1957 0.08849 0.08208 -0.0308 0.0127 0.7578 17.250 1.2016 0.09098 0.08464 -0.0312 0.0127 0.7580