XFOIL Version 6.94 Calculated polar for: EPPLER 541 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.3733 0.02289 0.01751 -0.0655 0.7908 0.8270 0.500 0.4311 0.02257 0.01722 -0.0667 0.7847 0.8317 1.000 0.5033 0.02216 0.01680 -0.0705 0.7795 0.8351 1.500 0.5604 0.02180 0.01643 -0.0714 0.7737 0.8398 2.000 0.4579 0.02176 0.01645 -0.0419 0.7594 0.8496 2.500 0.5440 0.02099 0.01568 -0.0482 0.7547 0.8509 3.000 0.5543 0.02071 0.01551 -0.0402 0.7432 0.8528 3.500 0.6270 0.01989 0.01473 -0.0438 0.7356 0.8547 4.000 0.6353 0.01935 0.01428 -0.0354 0.7245 0.8569 4.500 0.6833 0.01841 0.01338 -0.0343 0.7139 0.8589 5.000 0.7011 0.01770 0.01278 -0.0278 0.7004 0.8611 5.500 0.7572 0.01673 0.01186 -0.0284 0.6870 0.8622 6.000 0.7963 0.01587 0.01109 -0.0257 0.6681 0.8643 6.500 0.8118 0.01522 0.01058 -0.0187 0.6420 0.8666 7.000 0.8294 0.01468 0.01006 -0.0119 0.6042 0.8682 7.500 0.8389 0.01461 0.00984 -0.0038 0.5423 0.8701 8.000 0.8355 0.01552 0.01039 0.0058 0.4640 0.8724 8.500 0.8256 0.01706 0.01161 0.0154 0.3906 0.8759 9.000 0.8223 0.01894 0.01319 0.0227 0.3202 0.8784 9.500 0.8262 0.02094 0.01493 0.0282 0.2545 0.8807 10.000 0.8352 0.02302 0.01677 0.0325 0.1950 0.8829 10.500 0.8470 0.02524 0.01876 0.0361 0.1407 0.8850 11.000 0.8592 0.02767 0.02097 0.0393 0.0956 0.8869 11.500 0.8709 0.03028 0.02345 0.0423 0.0639 0.8889 12.000 0.8797 0.03300 0.02612 0.0456 0.0468 0.8921 12.500 0.8931 0.03570 0.02890 0.0480 0.0356 0.8949 13.000 0.9051 0.03876 0.03204 0.0500 0.0281 0.8975 13.500 0.9162 0.04215 0.03553 0.0515 0.0215 0.9003 14.000 0.9248 0.04606 0.03962 0.0528 0.0159 0.9031 14.500 0.9288 0.05067 0.04435 0.0536 0.0127 0.9058 15.000 0.9367 0.05526 0.04920 0.0538 0.0109 0.9085 15.500 0.9394 0.06046 0.05461 0.0540 0.0095 0.9120 16.000 0.9437 0.06583 0.06031 0.0538 0.0088 0.9158 16.500 0.9450 0.07193 0.06664 0.0527 0.0081 0.9197 17.000 0.9455 0.07866 0.07367 0.0509 0.0080 0.9237 17.500 0.9348 0.08749 0.08286 0.0479 0.0077 0.9274 18.000 0.9117 0.09865 0.09451 0.0431 0.0076 0.9335 18.500 0.8891 0.11055 0.10680 0.0369 0.0076 0.9416 19.000 0.8608 0.12484 0.12151 0.0282 0.0077 0.9519 20.000 0.5893 0.20231 0.20010 -0.0319 0.0248 0.8929 20.500 0.5825 0.21374 0.21153 -0.0395 0.0227 0.8933 21.000 0.5968 0.21963 0.21746 -0.0430 0.0215 0.8946 21.500 0.6001 0.22912 0.22696 -0.0487 0.0203 0.8954 22.000 0.6106 0.23632 0.23420 -0.0531 0.0188 0.8966 22.500 0.6251 0.24294 0.24085 -0.0565 0.0181 0.8981 23.000 0.6290 0.25259 0.25051 -0.0623 0.0166 0.8991 23.500 0.6403 0.25980 0.25777 -0.0666 0.0156 0.9005 24.000 0.6529 0.26725 0.26525 -0.0706 0.0151 0.9020 24.500 0.6594 0.27690 0.27492 -0.0760 0.0140 0.9032 25.000 0.6703 0.28473 0.28279 -0.0805 0.0130 0.9047 25.500 0.6800 0.29360 0.29168 -0.0852 0.0119 0.9061 26.000 0.6903 0.30228 0.30040 -0.0898 0.0107 0.9074 26.500 0.7007 0.30930 0.30746 -0.0935 0.0101 0.9094 27.000 0.7065 0.31881 0.31698 -0.0977 0.0097 0.9113 27.500 0.7135 0.32703 0.32524 -0.1012 0.0086 0.9136 28.000 0.7204 0.33441 0.33266 -0.1046 0.0081 0.9164 28.500 0.7279 0.34135 0.33964 -0.1078 0.0078 0.9197 29.000 0.7341 0.35051 0.34881 -0.1118 0.0077 0.9226 29.500 0.7415 0.35997 0.35831 -0.1160 0.0073 0.9252 30.000 0.7493 0.36923 0.36760 -0.1203 0.0067 0.9276 30.500 0.7525 0.37572 0.37412 -0.1227 0.0063 0.9318 31.000 0.7559 0.38226 0.38069 -0.1253 0.0060 0.9367 31.500 0.7604 0.38917 0.38764 -0.1284 0.0058 0.9419 32.500 0.7652 0.40294 0.40144 -0.1334 0.0057 0.9560 33.000 0.7676 0.40998 0.40850 -0.1361 0.0056 0.9660 34.000 0.7774 0.42678 0.42535 -0.1437 0.0053 1.0000 34.500 0.7845 0.43703 0.43563 -0.1487 0.0050 1.0000 35.000 0.7912 0.44725 0.44588 -0.1536 0.0048 1.0000 35.500 0.7973 0.45730 0.45596 -0.1584 0.0047 1.0000 36.000 0.8028 0.46728 0.46597 -0.1631 0.0045 1.0000 36.500 0.8077 0.47707 0.47578 -0.1676 0.0043 1.0000 37.000 0.8117 0.48648 0.48522 -0.1720 0.0042 1.0000 37.500 0.8152 0.49563 0.49440 -0.1762 0.0042 1.0000 38.000 0.8179 0.50445 0.50324 -0.1803 0.0041 1.0000 38.500 0.8200 0.51311 0.51193 -0.1840 0.0040 1.0000 40.500 0.8242 0.54717 0.54606 -0.1985 0.0039 1.0000 41.000 0.8244 0.55539 0.55431 -0.2018 0.0039 1.0000 41.500 0.8241 0.56309 0.56203 -0.2051 0.0039 1.0000 42.000 0.8234 0.57059 0.56956 -0.2083 0.0038 1.0000 42.500 0.8224 0.57822 0.57721 -0.2113 0.0036 1.0000 43.000 0.8208 0.58503 0.58404 -0.2144 0.0035 1.0000 43.500 0.8189 0.59181 0.59085 -0.2174 0.0033 1.0000 44.000 0.8165 0.59817 0.59723 -0.2203 0.0032 1.0000 44.500 0.8139 0.60439 0.60347 -0.2231 0.0030 1.0000 45.000 0.8109 0.61026 0.60936 -0.2259 0.0030 1.0000 45.500 0.8074 0.61561 0.61474 -0.2286 0.0029 1.0000 46.000 0.8038 0.62084 0.61999 -0.2313 0.0028 1.0000 46.500 0.7997 0.62561 0.62478 -0.2340 0.0027 1.0000 47.000 0.7950 0.62993 0.62912 -0.2366 0.0026 1.0000 47.500 0.7901 0.63406 0.63327 -0.2391 0.0025 1.0000