XFOIL Version 6.94 Calculated polar for: WORTMANN FX 63-137 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.9126 0.00930 0.00340 -0.2064 0.6620 0.5410 0.500 0.9681 0.00942 0.00354 -0.2061 0.6470 0.5602 1.000 1.0229 0.00960 0.00371 -0.2056 0.6312 0.5804 1.500 1.0757 0.00982 0.00387 -0.2047 0.6093 0.6005 2.000 1.1285 0.01009 0.00406 -0.2040 0.5877 0.6167 2.500 1.1807 0.01034 0.00430 -0.2031 0.5651 0.6312 3.000 1.2310 0.01068 0.00457 -0.2020 0.5390 0.6443 3.500 1.2808 0.01109 0.00491 -0.2007 0.5112 0.6600 4.000 1.3284 0.01157 0.00533 -0.1991 0.4835 0.6762 4.500 1.3764 0.01205 0.00579 -0.1976 0.4593 0.6920 5.000 1.4223 0.01261 0.00631 -0.1958 0.4271 0.7097 5.500 1.4655 0.01328 0.00694 -0.1935 0.4009 0.7303 6.000 1.5031 0.01415 0.00771 -0.1903 0.3581 0.7561 7.000 1.5548 0.01652 0.00979 -0.1797 0.2604 0.8315 8.000 1.5778 0.02004 0.01292 -0.1654 0.1646 1.0000 8.500 1.5919 0.02246 0.01509 -0.1598 0.1278 1.0000 9.000 1.6092 0.02483 0.01736 -0.1551 0.0974 1.0000 10.000 1.6375 0.03065 0.02306 -0.1466 0.0615 1.0000 10.500 1.6526 0.03385 0.02628 -0.1431 0.0559 1.0000 11.000 1.6698 0.03705 0.02962 -0.1403 0.0527 1.0000 11.500 1.6814 0.04100 0.03368 -0.1375 0.0483 1.0000 12.000 1.6966 0.04482 0.03761 -0.1353 0.0440 1.0000 12.500 1.7124 0.04875 0.04164 -0.1336 0.0382 1.0000 13.000 1.7179 0.05412 0.04694 -0.1319 0.0213 1.0000 13.500 1.6937 0.06381 0.05668 -0.1304 0.0031 1.0000 14.000 1.6955 0.07064 0.06373 -0.1301 0.0022 1.0000 14.500 1.6974 0.07779 0.07110 -0.1303 0.0019 1.0000 15.000 1.6970 0.08562 0.07918 -0.1310 0.0017 1.0000 15.500 1.6952 0.09396 0.08777 -0.1324 0.0016 1.0000 16.000 1.6926 0.10267 0.09673 -0.1343 0.0016 1.0000 16.500 1.6887 0.11172 0.10605 -0.1369 0.0015 1.0000 17.000 1.6832 0.12118 0.11578 -0.1400 0.0015 1.0000 17.500 1.6768 0.13086 0.12573 -0.1438 0.0015 1.0000 18.000 1.6680 0.14105 0.13618 -0.1483 0.0014 1.0000 18.500 1.6584 0.15142 0.14681 -0.1535 0.0014 1.0000 19.000 1.6472 0.16216 0.15781 -0.1595 0.0014 1.0000 19.500 1.6324 0.17375 0.16967 -0.1666 0.0014 1.0000 20.000 1.6182 0.18532 0.18148 -0.1741 0.0014 1.0000 20.500 1.6012 0.19775 0.19416 -0.1826 0.0014 1.0000 21.000 1.5846 0.21026 0.20690 -0.1916 0.0014 1.0000 21.500 1.5683 0.22292 0.21977 -0.2009 0.0015 1.0000 22.000 1.5542 0.23517 0.23221 -0.2102 0.0015 1.0000 22.500 1.5440 0.24660 0.24378 -0.2189 0.0015 1.0000 23.000 1.5397 0.25627 0.25355 -0.2265 0.0015 1.0000 23.500 1.5399 0.26465 0.26201 -0.2332 0.0015 1.0000 24.000 1.5441 0.27157 0.26897 -0.2389 0.0015 1.0000 24.500 1.5505 0.27762 0.27506 -0.2441 0.0015 1.0000 25.000 1.5570 0.28354 0.28104 -0.2492 0.0015 1.0000 25.500 1.5651 0.28868 0.28623 -0.2539 0.0015 1.0000 26.000 1.5724 0.29396 0.29157 -0.2587 0.0015 1.0000 26.500 1.5780 0.29971 0.29741 -0.2640 0.0016 1.0000 27.000 1.5830 0.30553 0.30332 -0.2694 0.0016 1.0000 27.500 1.5867 0.31171 0.30960 -0.2751 0.0016 1.0000 28.000 1.5884 0.31886 0.31687 -0.2815 0.0016 1.0000 28.500 1.5869 0.32775 0.32591 -0.2889 0.0017 1.0000 29.500 1.1398 0.54928 0.54842 -0.2684 0.0063 1.0000 30.000 1.1404 0.56214 0.56130 -0.2709 0.0058 1.0000 30.500 1.1409 0.57364 0.57282 -0.2732 0.0055 1.0000 31.000 1.1414 0.58344 0.58265 -0.2753 0.0053 1.0000 31.500 1.1406 0.59823 0.59744 -0.2778 0.0052 1.0000 32.000 1.1400 0.61514 0.61436 -0.2805 0.0047 1.0000 32.500 1.1392 0.62696 0.62621 -0.2827 0.0042 1.0000 33.000 1.1380 0.63757 0.63684 -0.2849 0.0040 1.0000 33.500 1.1366 0.64691 0.64621 -0.2867 0.0039 1.0000 34.000 1.1345 0.66335 0.66265 -0.2892 0.0038 1.0000 34.500 1.1329 0.67944 0.67875 -0.2914 0.0034 1.0000 35.000 1.1307 0.69193 0.69126 -0.2935 0.0031 1.0000 35.500 1.1279 0.70293 0.70228 -0.2955 0.0029 1.0000 36.000 1.1245 0.71216 0.71154 -0.2973 0.0027 1.0000 37.000 1.1176 0.73860 0.73801 -0.3012 0.0026 1.0000 37.500 1.1137 0.74977 0.74920 -0.3031 0.0026 1.0000 38.000 1.1101 0.76282 0.76226 -0.3049 0.0025 1.0000 38.500 1.1057 0.77382 0.77328 -0.3066 0.0024 1.0000 39.000 1.1011 0.78495 0.78443 -0.3083 0.0022 1.0000 39.500 1.0959 0.79495 0.79445 -0.3100 0.0021 1.0000 40.000 1.0905 0.80473 0.80425 -0.3116 0.0020 1.0000 40.500 1.0848 0.81423 0.81377 -0.3132 0.0019 1.0000 41.000 1.0786 0.82250 0.82207 -0.3147 0.0019 1.0000 41.500 1.0723 0.83114 0.83073 -0.3162 0.0019 1.0000 42.000 1.0656 0.83928 0.83888 -0.3177 0.0018 1.0000 42.500 1.0586 0.84672 0.84634 -0.3191 0.0017 1.0000 43.000 1.0513 0.85380 0.85344 -0.3205 0.0017 1.0000 43.500 1.0438 0.86051 0.86017 -0.3218 0.0017 1.0000 44.000 1.0355 0.86576 0.86544 -0.3231 0.0016 1.0000 46.000 1.0031 0.89253 0.89228 -0.3277 0.0016 1.0000 46.500 0.9951 0.89933 0.89910 -0.3286 0.0015 1.0000 47.000 0.9867 0.90531 0.90511 -0.3295 0.0012 1.0000 47.500 0.9776 0.90976 0.90957 -0.3304 0.0010 1.0000 48.000 0.9679 0.91252 0.91235 -0.3314 0.0009 1.0000 48.500 0.9572 0.91334 0.91319 -0.3324 0.0009 1.0000 49.000 0.9502 0.92594 0.92578 -0.3327 0.0007 1.0000 49.500 0.9405 0.92922 0.92908 -0.3334 0.0006 1.0000 50.000 0.9305 0.93174 0.93161 -0.3341 0.0005 1.0000 50.500 0.9196 0.93170 0.93159 -0.3348 0.0004 1.0000 51.000 0.9089 0.93200 0.93190 -0.3354 0.0004 1.0000 51.500 0.8972 0.93043 0.93036 -0.3360 0.0003 1.0000 52.500 0.8769 0.93566 0.93559 -0.3368 0.0003 1.0000 53.000 0.8664 0.93637 0.93632 -0.3371 0.0003 1.0000 53.500 0.8554 0.93584 0.93580 -0.3373 0.0003 1.0000 54.000 0.8445 0.93532 0.93530 -0.3376 0.0003 1.0000 54.500 0.8332 0.93343 0.93342 -0.3378 0.0003 1.0000 55.000 0.8215 0.93005 0.93005 -0.3380 0.0002 1.0000 55.500 0.8096 0.92614 0.92616 -0.3381 0.0002 1.0000 56.000 0.7977 0.92196 0.92199 -0.3382 0.0002 1.0000 56.500 0.7856 0.91713 0.91717 -0.3383 0.0002 1.0000 57.000 0.7734 0.91182 0.91188 -0.3383 0.0002 1.0000 57.500 0.7611 0.90597 0.90604 -0.3383 0.0001 1.0000 58.000 0.7487 0.89948 0.89956 -0.3383 0.0001 1.0000 58.500 0.7361 0.89222 0.89231 -0.3382 0.0001 1.0000 59.000 0.7233 0.88443 0.88453 -0.3381 0.0001 1.0000 59.500 0.7104 0.87600 0.87611 -0.3380 0.0001 1.0000 60.000 0.6972 0.86711 0.86723 -0.3379 0.0001 1.0000