XFOIL Version 6.96 Calculated polar for: WORTMANN FX 63-137 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.5605 0.07422 0.07208 -0.0847 0.9955 0.0071 -13.250 -0.6564 0.04706 0.04445 -0.1106 0.9887 0.0068 -13.000 -0.6591 0.03837 0.03554 -0.1235 0.9843 0.0068 -12.750 -0.6590 0.03317 0.03018 -0.1304 0.9748 0.0068 -12.500 -0.6470 0.02858 0.02542 -0.1380 0.9652 0.0069 -12.250 -0.6190 0.02474 0.02141 -0.1469 0.9595 0.0069 -12.000 -0.5901 0.02191 0.01840 -0.1539 0.9504 0.0069 -11.750 -0.5501 0.01978 0.01609 -0.1608 0.9466 0.0070 -11.500 -0.5101 0.01826 0.01442 -0.1660 0.9427 0.0071 -11.250 -0.4712 0.01692 0.01293 -0.1704 0.9357 0.0072 -11.000 -0.4255 0.01580 0.01167 -0.1758 0.9309 0.0074 -10.750 -0.3785 0.01483 0.01056 -0.1811 0.9249 0.0075 -10.500 -0.3340 0.01402 0.00961 -0.1856 0.9158 0.0077 -10.250 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0.2957 0.00918 0.00347 -0.1991 0.7424 0.0221 -5.000 0.3261 0.00896 0.00321 -0.1997 0.7352 0.0231 -4.750 0.3558 0.00882 0.00301 -0.2002 0.7282 0.0238 -4.500 0.3859 0.00867 0.00283 -0.2006 0.7205 0.0243 -4.250 0.4153 0.00858 0.00267 -0.2010 0.7130 0.0247 -4.000 0.4456 0.00845 0.00253 -0.2014 0.7064 0.0252 -3.750 0.4755 0.00835 0.00239 -0.2018 0.6993 0.0261 -3.500 0.5053 0.00827 0.00230 -0.2022 0.6933 0.0274 -3.250 0.5352 0.00820 0.00223 -0.2026 0.6871 0.0300 -3.000 0.5642 0.00817 0.00217 -0.2028 0.6804 0.0340 -2.750 0.5941 0.00811 0.00209 -0.2032 0.6742 0.0378 -2.500 0.6235 0.00808 0.00203 -0.2034 0.6675 0.0409 -2.250 0.6529 0.00805 0.00197 -0.2037 0.6617 0.0444 -2.000 0.6832 0.00797 0.00193 -0.2042 0.6555 0.0530 -1.750 0.7125 0.00795 0.00190 -0.2045 0.6485 0.0687 -1.500 0.7430 0.00785 0.00187 -0.2051 0.6420 0.0971 -1.250 0.7738 0.00774 0.00184 -0.2058 0.6338 0.1424 -1.000 0.8061 0.00751 0.00182 -0.2070 0.6257 0.2327 -0.750 0.8372 0.00738 0.00182 -0.2079 0.6173 0.3054 -0.500 0.8675 0.00731 0.00187 -0.2085 0.6098 0.3678 -0.250 0.8970 0.00730 0.00193 -0.2089 0.6016 0.4063 0.000 0.9255 0.00736 0.00200 -0.2090 0.5921 0.4363 0.250 0.9531 0.00746 0.00208 -0.2090 0.5740 0.4573 0.500 0.9799 0.00762 0.00218 -0.2087 0.5532 0.4818 0.750 1.0070 0.00776 0.00229 -0.2085 0.5396 0.5006 1.000 1.0340 0.00792 0.00240 -0.2083 0.5271 0.5107 1.250 1.0611 0.00807 0.00251 -0.2082 0.5127 0.5199 1.500 1.0878 0.00825 0.00262 -0.2079 0.4960 0.5273 1.750 1.1142 0.00845 0.00276 -0.2076 0.4813 0.5361 2.000 1.1408 0.00863 0.00289 -0.2074 0.4683 0.5452 2.250 1.1675 0.00881 0.00304 -0.2071 0.4542 0.5553 2.750 1.2175 0.00939 0.00342 -0.2061 0.4131 0.5741 3.000 1.2430 0.00964 0.00362 -0.2057 0.3984 0.5805 3.250 1.2687 0.00987 0.00381 -0.2053 0.3812 0.5889 3.500 1.2932 0.01018 0.00403 -0.2047 0.3606 0.5983 3.750 1.3179 0.01048 0.00427 -0.2042 0.3463 0.6078 4.000 1.3425 0.01077 0.00451 -0.2036 0.3325 0.6154 4.250 1.3666 0.01110 0.00476 -0.2030 0.3090 0.6228 4.500 1.3889 0.01155 0.00508 -0.2021 0.2879 0.6297 4.750 1.4124 0.01189 0.00538 -0.2014 0.2715 0.6368 5.000 1.4331 0.01243 0.00577 -0.2002 0.2408 0.6441 5.250 1.4548 0.01288 0.00614 -0.1991 0.2260 0.6514 5.500 1.4779 0.01321 0.00645 -0.1984 0.2128 0.6598 5.750 1.4967 0.01382 0.00693 -0.1969 0.1863 0.6680 6.000 1.5176 0.01427 0.00733 -0.1957 0.1737 0.6776 6.250 1.5386 0.01467 0.00772 -0.1946 0.1629 0.6873 6.500 1.5531 0.01542 0.00831 -0.1923 0.1353 0.6982 6.750 1.5701 0.01589 0.00877 -0.1904 0.1265 0.7108 7.000 1.5890 0.01627 0.00919 -0.1889 0.1183 0.7250 7.250 1.6002 0.01705 0.00988 -0.1861 0.0977 0.7403 7.500 1.6144 0.01770 0.01051 -0.1838 0.0869 0.7571 7.750 1.6284 0.01835 0.01118 -0.1816 0.0792 0.7756 8.000 1.6449 0.01888 0.01176 -0.1798 0.0690 0.7981 8.250 1.6575 0.01962 0.01250 -0.1775 0.0638 0.8261 8.500 1.6708 0.02021 0.01319 -0.1752 0.0597 0.8750 8.750 1.6781 0.02069 0.01380 -0.1718 0.0584 1.0000 9.000 1.6921 0.02146 0.01459 -0.1699 0.0570 1.0000 9.250 1.7040 0.02237 0.01551 -0.1678 0.0550 1.0000 9.500 1.7158 0.02333 0.01648 -0.1658 0.0529 1.0000 9.750 1.7277 0.02431 0.01750 -0.1638 0.0513 1.0000 10.000 1.7406 0.02523 0.01847 -0.1621 0.0503 1.0000 10.250 1.7550 0.02608 0.01936 -0.1607 0.0498 1.0000 10.500 1.7687 0.02701 0.02034 -0.1592 0.0491 1.0000 10.750 1.7816 0.02801 0.02139 -0.1577 0.0480 1.0000 11.000 1.7935 0.02913 0.02256 -0.1562 0.0468 1.0000 11.250 1.8035 0.03044 0.02389 -0.1545 0.0450 1.0000 11.500 1.8118 0.03194 0.02542 -0.1529 0.0431 1.0000 11.750 1.8225 0.03328 0.02680 -0.1515 0.0415 1.0000 12.000 1.8368 0.03430 0.02786 -0.1505 0.0399 1.0000 12.250 1.8462 0.03581 0.02935 -0.1492 0.0360 1.0000 12.500 1.8523 0.03768 0.03118 -0.1477 0.0294 1.0000 12.750 1.8444 0.04104 0.03443 -0.1455 0.0177 1.0000 13.000 1.8282 0.04551 0.03891 -0.1431 0.0055 1.0000 13.250 1.8274 0.04848 0.04196 -0.1418 0.0041 1.0000 13.500 1.8301 0.05113 0.04469 -0.1408 0.0038 1.0000 13.750 1.8311 0.05406 0.04771 -0.1399 0.0034 1.0000 14.000 1.8340 0.05685 0.05059 -0.1391 0.0032 1.0000 14.250 1.8373 0.05964 0.05347 -0.1386 0.0031 1.0000 14.500 1.8392 0.06270 0.05662 -0.1381 0.0030 1.0000 14.750 1.8400 0.06597 0.05999 -0.1377 0.0029 1.0000 15.000 1.8407 0.06934 0.06345 -0.1375 0.0029 1.0000 15.250 1.8399 0.07302 0.06722 -0.1374 0.0028 1.0000 15.500 1.8376 0.07699 0.07130 -0.1374 0.0027 1.0000 15.750 1.8350 0.08110 0.07552 -0.1377 0.0026 1.0000 16.000 1.8323 0.08530 0.07982 -0.1380 0.0026 1.0000 16.250 1.8275 0.08992 0.08456 -0.1386 0.0025 1.0000 16.500 1.8224 0.09468 0.08944 -0.1394 0.0025 1.0000 16.750 1.8142 0.10005 0.09494 -0.1404 0.0024 1.0000 17.000 1.8063 0.10543 0.10044 -0.1417 0.0024 1.0000