XFOIL Version 6.94 Calculated polar for: WORTMANN FX 72-MS-150A AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 1.0386 0.01488 0.00806 -0.2202 0.6093 0.5963 1.000 1.0904 0.01533 0.00855 -0.2196 0.6053 0.6317 1.500 1.1457 0.01566 0.00881 -0.2199 0.6016 0.6464 2.000 1.2014 0.01596 0.00906 -0.2204 0.5983 0.6575 2.500 1.2584 0.01641 0.00943 -0.2213 0.5952 0.6686 3.000 1.3116 0.01709 0.01014 -0.2216 0.5921 0.6789 3.500 1.3611 0.01761 0.01080 -0.2212 0.5893 0.6907 4.000 1.4098 0.01822 0.01152 -0.2208 0.5860 0.7054 4.500 1.4590 0.01878 0.01222 -0.2204 0.5826 0.7239 5.000 1.5113 0.01908 0.01264 -0.2204 0.5785 0.7474 5.500 1.5659 0.01939 0.01308 -0.2208 0.5752 0.7876 6.000 1.6171 0.01999 0.01392 -0.2208 0.5722 1.0000 6.500 1.6582 0.02107 0.01517 -0.2193 0.5689 1.0000 7.000 1.6948 0.02182 0.01607 -0.2168 0.5631 1.0000 7.500 1.7550 0.02108 0.01529 -0.2175 0.5545 1.0000 8.000 1.8011 0.02145 0.01574 -0.2164 0.5470 1.0000 8.500 1.8316 0.02159 0.01604 -0.2123 0.5377 1.0000 9.000 1.8786 0.02119 0.01561 -0.2108 0.5261 1.0000 9.500 1.8785 0.02165 0.01625 -0.2013 0.5150 1.0000 10.000 1.8866 0.02231 0.01703 -0.1939 0.5022 1.0000 10.500 1.8846 0.02361 0.01838 -0.1858 0.4847 1.0000 11.000 1.8626 0.02680 0.02172 -0.1766 0.4616 1.0000 11.500 1.8331 0.03168 0.02665 -0.1682 0.4244 1.0000 12.000 1.7862 0.03927 0.03398 -0.1599 0.3632 1.0000 12.500 1.7311 0.04935 0.04378 -0.1533 0.3080 1.0000 13.000 1.6772 0.06085 0.05501 -0.1486 0.2527 1.0000 13.500 1.6254 0.07340 0.06724 -0.1458 0.1905 1.0000 14.000 1.5792 0.08629 0.07969 -0.1443 0.1190 1.0000 14.500 1.5389 0.09907 0.09191 -0.1440 0.0403 1.0000 15.000 1.5326 0.10735 0.10015 -0.1441 0.0253 1.0000 15.500 1.5379 0.11393 0.10688 -0.1445 0.0223 1.0000 16.000 1.5428 0.12063 0.11375 -0.1451 0.0206 1.0000 16.500 1.5473 0.12732 0.12059 -0.1460 0.0193 1.0000 17.000 1.5474 0.13472 0.12813 -0.1474 0.0186 1.0000 17.500 1.5534 0.14102 0.13460 -0.1486 0.0181 1.0000 18.000 1.5607 0.14696 0.14068 -0.1500 0.0176 1.0000 18.500 1.5718 0.15201 0.14583 -0.1511 0.0172 1.0000 19.000 1.5864 0.15621 0.15012 -0.1520 0.0168 1.0000 19.500 1.6061 0.15918 0.15313 -0.1524 0.0165 1.0000 20.000 1.6327 0.16054 0.15451 -0.1521 0.0162 1.0000 20.500 1.6700 0.15959 0.15358 -0.1506 0.0159 1.0000 21.000 1.7087 0.15854 0.15265 -0.1492 0.0158 1.0000 21.500 1.7379 0.15949 0.15384 -0.1489 0.0159 1.0000 22.000 1.7470 0.16425 0.15894 -0.1506 0.0160 1.0000 22.500 1.7480 0.17039 0.16551 -0.1532 0.0162 1.0000 23.000 1.7365 0.17882 0.17442 -0.1574 0.0164 1.0000 23.500 1.7048 0.19152 0.18775 -0.1646 0.0168 1.0000 24.000 1.6716 0.20512 0.20188 -0.1731 0.0174 1.0000 24.500 1.6412 0.21866 0.21583 -0.1824 0.0179 1.0000 25.000 1.6198 0.23047 0.22790 -0.1910 0.0184 1.0000 26.500 1.1341 0.41790 0.41667 -0.2327 0.0255 1.0000 27.000 1.1248 0.43772 0.43648 -0.2386 0.0227 1.0000 27.500 1.1243 0.45174 0.45052 -0.2418 0.0207 1.0000 29.500 1.1258 0.50358 0.50247 -0.2528 0.0148 1.0000 30.000 1.1263 0.51472 0.51363 -0.2551 0.0137 1.0000 30.500 1.1256 0.52912 0.52806 -0.2579 0.0126 1.0000 31.000 1.1254 0.54112 0.54009 -0.2602 0.0113 1.0000 31.500 1.1261 0.54987 0.54888 -0.2618 0.0109 1.0000 33.000 1.1214 0.59560 0.59465 -0.2697 0.0077 1.0000 34.000 1.1181 0.62260 0.62169 -0.2740 0.0063 1.0000 34.500 1.1162 0.63555 0.63467 -0.2761 0.0054 1.0000 35.000 1.1136 0.64390 0.64305 -0.2777 0.0048 1.0000 35.500 1.1109 0.65916 0.65832 -0.2799 0.0047 1.0000 36.000 1.1089 0.67566 0.67482 -0.2820 0.0035 1.0000 36.500 1.1057 0.68691 0.68610 -0.2839 0.0032 1.0000 37.000 1.1017 0.69608 0.69531 -0.2854 0.0030 1.0000 38.000 1.0950 0.72514 0.72439 -0.2893 0.0028 1.0000 38.500 1.0913 0.73770 0.73697 -0.2910 0.0025 1.0000 39.000 1.0866 0.74857 0.74787 -0.2926 0.0021 1.0000 40.000 1.0764 0.76876 0.76811 -0.2958 0.0017 1.0000 40.500 1.0704 0.77752 0.77690 -0.2973 0.0016 1.0000 41.500 1.0592 0.79952 0.79894 -0.3003 0.0015 1.0000 42.000 1.0536 0.80992 0.80935 -0.3017 0.0015 1.0000 42.500 1.0475 0.81950 0.81896 -0.3030 0.0012 1.0000 43.000 1.0408 0.82802 0.82750 -0.3043 0.0010 1.0000 43.500 1.0337 0.83565 0.83515 -0.3056 0.0008 1.0000 44.000 1.0262 0.84284 0.84238 -0.3069 0.0007 1.0000 45.500 1.0043 0.86778 0.86736 -0.3102 0.0004 1.0000 46.000 0.9958 0.87292 0.87253 -0.3113 0.0004 1.0000 46.500 0.9876 0.87925 0.87888 -0.3122 0.0003 1.0000 47.000 0.9789 0.88419 0.88384 -0.3132 0.0003 1.0000 47.500 0.9700 0.88875 0.88843 -0.3142 0.0002 1.0000 48.000 0.9603 0.89206 0.89176 -0.3151 0.0001 1.0000 48.500 0.9500 0.89457 0.89430 -0.3159 0.0001 1.0000 50.000 0.9225 0.90582 0.90560 -0.3180 0.0001 1.0000 50.500 0.9126 0.90789 0.90769 -0.3187 0.0000 1.0000 51.000 0.9022 0.90895 0.90877 -0.3193 0.0000 1.0000 51.500 0.8916 0.90917 0.90901 -0.3199 0.0000 1.0000 52.000 0.8808 0.90899 0.90886 -0.3205 0.0000 1.0000 54.000 0.8366 0.90440 0.90434 -0.3221 0.0000 1.0000 54.500 0.8250 0.90155 0.90151 -0.3224 0.0000 1.0000 55.000 0.8136 0.89890 0.89888 -0.3227 0.0000 1.0000 55.500 0.8018 0.89529 0.89529 -0.3230 0.0000 1.0000 56.000 0.7898 0.89060 0.89061 -0.3232 0.0000 1.0000 56.500 0.7779 0.88638 0.88641 -0.3233 0.0000 1.0000 57.000 0.7658 0.88125 0.88131 -0.3234 0.0000 1.0000 57.500 0.7537 0.87579 0.87586 -0.3235 0.0000 1.0000 58.000 0.7411 0.86886 0.86895 -0.3235 0.0000 1.0000 58.500 0.7288 0.86253 0.86264 -0.3235 0.0000 1.0000 59.000 0.7163 0.85545 0.85557 -0.3234 0.0000 1.0000 59.500 0.7037 0.84816 0.84830 -0.3233 0.0000 1.0000 60.000 0.6910 0.83993 0.84008 -0.3232 0.0000 1.0000