XFOIL Version 6.94 Calculated polar for: WORTMANN FX 05-188 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 0.4128 0.01605 0.01024 -0.0995 0.7180 0.7069 0.500 0.4700 0.01625 0.01041 -0.0994 0.7125 0.7124 1.000 0.5200 0.01640 0.01059 -0.0988 0.7036 0.7207 1.500 0.5767 0.01622 0.01040 -0.0996 0.6957 0.7277 2.000 0.6360 0.01628 0.01043 -0.1002 0.6897 0.7321 2.500 0.6813 0.01655 0.01081 -0.0987 0.6813 0.7390 3.000 0.7407 0.01646 0.01073 -0.1004 0.6736 0.7471 3.500 0.8000 0.01641 0.01068 -0.1010 0.6674 0.7510 4.000 0.8414 0.01662 0.01108 -0.0987 0.6580 0.7564 4.500 0.9032 0.01636 0.01082 -0.1003 0.6494 0.7636 5.000 0.9543 0.01618 0.01076 -0.0999 0.6385 0.7690 5.500 1.0085 0.01577 0.01039 -0.0994 0.6271 0.7732 6.000 1.0533 0.01524 0.00991 -0.0972 0.6068 0.7784 7.000 1.1356 0.01508 0.00978 -0.0925 0.5599 0.7892 7.500 1.1547 0.01528 0.01005 -0.0858 0.5330 0.7940 8.000 1.1740 0.01584 0.01059 -0.0798 0.5011 0.7995 8.500 1.1845 0.01697 0.01162 -0.0733 0.4571 0.8050 9.000 1.1812 0.01876 0.01325 -0.0655 0.4042 0.8092 9.500 1.1681 0.02155 0.01581 -0.0574 0.3460 0.8140 10.000 1.1440 0.02569 0.01955 -0.0498 0.2646 0.8185 10.500 1.1199 0.03072 0.02412 -0.0437 0.1821 0.8229 11.000 1.1061 0.03581 0.02878 -0.0396 0.1118 0.8258 11.500 1.1004 0.04054 0.03329 -0.0365 0.0720 0.8288 12.000 1.1050 0.04484 0.03752 -0.0343 0.0532 0.8326 12.500 1.1171 0.04884 0.04158 -0.0332 0.0462 0.8363 13.000 1.1309 0.05299 0.04582 -0.0326 0.0422 0.8399 13.500 1.1439 0.05748 0.05042 -0.0323 0.0398 0.8434 14.000 1.1579 0.06187 0.05493 -0.0322 0.0379 0.8470 14.500 1.1700 0.06646 0.05958 -0.0319 0.0363 0.8510 15.000 1.1895 0.07045 0.06376 -0.0321 0.0348 0.8558 15.500 1.2112 0.07432 0.06773 -0.0324 0.0336 0.8615 16.000 1.2365 0.07765 0.07112 -0.0325 0.0326 0.8669 16.500 1.2704 0.07990 0.07345 -0.0322 0.0317 0.8729 17.000 1.2963 0.08360 0.07741 -0.0327 0.0311 0.8800 17.500 1.3194 0.08753 0.08164 -0.0330 0.0306 0.8880 18.000 1.3375 0.09215 0.08658 -0.0336 0.0301 0.8981 18.500 1.3468 0.09749 0.09223 -0.0342 0.0296 0.9125 19.000 1.3454 0.10250 0.09758 -0.0339 0.0291 1.0000 19.500 1.3507 0.10978 0.10514 -0.0372 0.0287 1.0000 20.000 1.3430 0.11893 0.11465 -0.0416 0.0286 1.0000 20.500 1.3116 0.13191 0.12814 -0.0484 0.0287 1.0000 21.000 1.2247 0.15618 0.15321 -0.0632 0.0296 1.0000 21.500 1.0820 0.19960 0.19728 -0.0917 0.0322 1.0000 22.000 0.9793 0.25142 0.24904 -0.1181 0.0430 1.0000 22.500 1.0042 0.25539 0.25302 -0.1207 0.0418 1.0000 23.000 1.0022 0.26575 0.26333 -0.1290 0.0384 1.0000 23.500 1.0233 0.26987 0.26748 -0.1320 0.0369 1.0000 24.000 1.0269 0.27865 0.27623 -0.1389 0.0336 1.0000 24.500 1.0489 0.28211 0.27972 -0.1413 0.0322 1.0000 25.000 1.0528 0.29029 0.28787 -0.1481 0.0286 1.0000 25.500 1.0625 0.29734 0.29491 -0.1533 0.0258 1.0000 26.000 1.0796 0.30106 0.29865 -0.1566 0.0241 1.0000 26.500 1.0861 0.30920 0.30676 -0.1627 0.0215 1.0000 27.000 1.1021 0.31286 0.31044 -0.1660 0.0204 1.0000 27.500 1.1088 0.32099 0.31854 -0.1720 0.0190 1.0000 28.000 1.1208 0.32602 0.32357 -0.1764 0.0177 1.0000 28.500 1.1344 0.32989 0.32746 -0.1801 0.0170 1.0000 29.000 1.1470 0.33515 0.33272 -0.1841 0.0167 1.0000 29.500 1.1532 0.34226 0.33981 -0.1902 0.0157 1.0000 30.000 1.1640 0.34704 0.34459 -0.1947 0.0147 1.0000 30.500 1.1747 0.35119 0.34876 -0.1990 0.0142 1.0000 31.000 1.1862 0.35482 0.35240 -0.2028 0.0138 1.0000 31.500 1.1989 0.35951 0.35711 -0.2063 0.0136 1.0000 32.000 1.2040 0.36478 0.36236 -0.2123 0.0135 1.0000 32.500 1.2128 0.36994 0.36753 -0.2172 0.0128 1.0000 33.000 1.2217 0.37417 0.37177 -0.2217 0.0121 1.0000 33.500 1.2304 0.37798 0.37559 -0.2261 0.0116 1.0000 34.000 1.2388 0.38122 0.37885 -0.2303 0.0111 1.0000 34.500 1.2476 0.38429 0.38195 -0.2340 0.0109 1.0000 35.000 1.2547 0.38853 0.38619 -0.2386 0.0107 1.0000 35.500 1.2612 0.39323 0.39090 -0.2439 0.0103 1.0000 36.000 1.2684 0.39667 0.39435 -0.2484 0.0095 1.0000 36.500 1.2750 0.39933 0.39702 -0.2527 0.0088 1.0000 37.000 1.2810 0.40135 0.39907 -0.2569 0.0084 1.0000 38.000 1.2925 0.40774 0.40548 -0.2660 0.0080 1.0000 38.500 1.2983 0.41103 0.40878 -0.2705 0.0073 1.0000 39.000 1.3032 0.41342 0.41119 -0.2749 0.0068 1.0000 41.000 0.9160 0.62330 0.62242 -0.2478 0.0041 1.0000 41.500 0.9141 0.63243 0.63157 -0.2503 0.0037 1.0000 42.000 0.9116 0.64053 0.63968 -0.2527 0.0032 1.0000 42.500 0.9087 0.64778 0.64696 -0.2551 0.0030 1.0000 43.000 0.9050 0.65405 0.65325 -0.2575 0.0029 1.0000 44.000 0.8980 0.67091 0.67015 -0.2619 0.0027 1.0000 44.500 0.8944 0.67872 0.67798 -0.2640 0.0026 1.0000 45.000 0.8900 0.68541 0.68469 -0.2661 0.0024 1.0000 45.500 0.8854 0.69168 0.69097 -0.2681 0.0022 1.0000 46.000 0.8803 0.69717 0.69648 -0.2702 0.0020 1.0000 46.500 0.8749 0.70212 0.70146 -0.2721 0.0018 1.0000 47.000 0.8689 0.70625 0.70560 -0.2741 0.0017 1.0000 48.000 0.8571 0.71696 0.71634 -0.2776 0.0017 1.0000 48.500 0.8508 0.72111 0.72051 -0.2793 0.0016 1.0000 49.000 0.8447 0.72600 0.72542 -0.2809 0.0016 1.0000 49.500 0.8380 0.72971 0.72915 -0.2824 0.0014 1.0000 50.000 0.8309 0.73261 0.73206 -0.2839 0.0013 1.0000 50.500 0.8237 0.73522 0.73469 -0.2855 0.0012 1.0000 51.000 0.8161 0.73697 0.73646 -0.2869 0.0011 1.0000 51.500 0.8083 0.73840 0.73791 -0.2883 0.0010 1.0000 52.000 0.8000 0.73882 0.73834 -0.2896 0.0009 1.0000 52.500 0.7915 0.73897 0.73851 -0.2910 0.0009 1.0000 54.500 0.7572 0.73984 0.73943 -0.2954 0.0008 1.0000 55.000 0.7482 0.73883 0.73843 -0.2964 0.0008 1.0000 55.500 0.7391 0.73755 0.73717 -0.2972 0.0008 1.0000 56.000 0.7297 0.73559 0.73523 -0.2981 0.0008 1.0000 56.500 0.7203 0.73341 0.73306 -0.2989 0.0007 1.0000 57.000 0.7105 0.73012 0.72978 -0.2997 0.0007 1.0000 57.500 0.7007 0.72696 0.72664 -0.3004 0.0006 1.0000 58.000 0.6907 0.72312 0.72280 -0.3010 0.0005 1.0000 58.500 0.6806 0.71892 0.71862 -0.3017 0.0005 1.0000 59.000 0.6703 0.71409 0.71380 -0.3022 0.0005 1.0000 59.500 0.6599 0.70876 0.70848 -0.3027 0.0004 1.0000 60.000 0.6495 0.70317 0.70291 -0.3032 0.0004 1.0000