XFOIL Version 6.94 Calculated polar for: OAF102 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 0.4707 0.00916 0.00318 -0.1184 0.7347 0.4527 0.500 0.5301 0.00917 0.00328 -0.1190 0.7220 0.4783 1.000 0.5888 0.00926 0.00339 -0.1194 0.7095 0.5071 1.500 0.6481 0.00923 0.00353 -0.1200 0.6968 0.5382 2.000 0.7070 0.00928 0.00372 -0.1204 0.6841 0.5779 2.500 0.7655 0.00921 0.00391 -0.1208 0.6686 0.6514 3.500 0.8700 0.00855 0.00384 -0.1182 0.5948 1.0000 4.000 0.9276 0.00887 0.00405 -0.1183 0.5488 1.0000 4.500 0.9828 0.00966 0.00444 -0.1183 0.4531 1.0000 5.000 1.0267 0.01301 0.00610 -0.1180 0.1371 1.0000 5.500 1.0757 0.01488 0.00746 -0.1174 0.0581 1.0000 6.000 1.1259 0.01623 0.00873 -0.1167 0.0434 1.0000 6.500 1.1754 0.01747 0.00999 -0.1157 0.0354 1.0000 7.000 1.2213 0.01902 0.01156 -0.1143 0.0304 1.0000 8.000 1.3065 0.02235 0.01506 -0.1103 0.0237 1.0000 8.500 1.3426 0.02458 0.01738 -0.1074 0.0218 1.0000 9.000 1.3791 0.02660 0.01953 -0.1045 0.0200 1.0000 9.500 1.4112 0.02917 0.02225 -0.1011 0.0185 1.0000 10.000 1.4417 0.03163 0.02496 -0.0975 0.0172 1.0000 10.500 1.4684 0.03438 0.02784 -0.0937 0.0164 1.0000 11.000 1.4882 0.03857 0.03240 -0.0892 0.0158 1.0000 11.500 1.4945 0.04324 0.03762 -0.0834 0.0153 1.0000 12.000 1.4889 0.04927 0.04422 -0.0780 0.0149 1.0000 12.500 1.4686 0.05694 0.05247 -0.0734 0.0147 1.0000 13.000 1.4322 0.06703 0.06315 -0.0707 0.0146 1.0000 13.500 1.3821 0.07999 0.07667 -0.0713 0.0148 1.0000 14.000 1.3271 0.09542 0.09257 -0.0762 0.0150 1.0000 14.500 1.2742 0.11352 0.11105 -0.0858 0.0153 1.0000 15.000 1.2243 0.13558 0.13341 -0.1005 0.0156 1.0000 15.500 1.1907 0.15660 0.15455 -0.1143 0.0160 1.0000 17.000 0.8178 0.20765 0.20577 -0.1121 0.0236 1.0000 17.500 0.8262 0.21258 0.21071 -0.1131 0.0228 1.0000 18.000 0.8202 0.22231 0.22044 -0.1175 0.0214 1.0000 18.500 0.8242 0.22887 0.22701 -0.1199 0.0200 1.0000 19.000 0.8340 0.23363 0.23179 -0.1206 0.0193 1.0000 19.500 0.8295 0.24376 0.24192 -0.1251 0.0180 1.0000 20.000 0.8342 0.25039 0.24856 -0.1273 0.0168 1.0000 21.000 0.8415 0.26535 0.26354 -0.1324 0.0150 1.0000 21.500 0.8464 0.27212 0.27033 -0.1346 0.0139 1.0000 22.500 0.8545 0.28708 0.28531 -0.1394 0.0124 1.0000 23.000 0.8591 0.29429 0.29253 -0.1417 0.0114 1.0000 23.500 0.8641 0.30074 0.29899 -0.1438 0.0108 1.0000 24.500 0.8719 0.31590 0.31418 -0.1484 0.0103 1.0000 25.000 0.8758 0.32396 0.32226 -0.1510 0.0095 1.0000 25.500 0.8799 0.33119 0.32950 -0.1532 0.0089 1.0000 26.000 0.8839 0.33808 0.33641 -0.1554 0.0085 1.0000 26.500 0.8879 0.34451 0.34286 -0.1574 0.0082 1.0000 27.000 0.8914 0.35190 0.35027 -0.1594 0.0080 1.0000 27.500 0.8940 0.36099 0.35937 -0.1623 0.0076 1.0000 28.000 0.8972 0.36862 0.36702 -0.1646 0.0068 1.0000 28.500 0.9002 0.37567 0.37409 -0.1668 0.0063 1.0000 29.000 0.9029 0.38225 0.38070 -0.1689 0.0060 1.0000 30.000 0.9070 0.39794 0.39642 -0.1733 0.0058 1.0000 30.500 0.9092 0.40620 0.40469 -0.1757 0.0056 1.0000 31.000 0.9113 0.41395 0.41247 -0.1779 0.0053 1.0000 31.500 0.9129 0.42138 0.41991 -0.1801 0.0049 1.0000 32.000 0.9142 0.42853 0.42709 -0.1823 0.0046 1.0000 32.500 0.9152 0.43531 0.43389 -0.1845 0.0042 1.0000 33.000 0.9157 0.44179 0.44040 -0.1867 0.0040 1.0000 34.000 0.9161 0.45664 0.45529 -0.1909 0.0039 1.0000 34.500 0.9165 0.46478 0.46345 -0.1931 0.0038 1.0000 35.000 0.9168 0.47243 0.47112 -0.1952 0.0036 1.0000 35.500 0.9165 0.47962 0.47833 -0.1973 0.0033 1.0000 36.000 0.9158 0.48648 0.48522 -0.1994 0.0030 1.0000 36.500 0.9149 0.49314 0.49190 -0.2015 0.0028 1.0000 37.000 0.9136 0.49961 0.49839 -0.2037 0.0027 1.0000 37.500 0.9120 0.50582 0.50463 -0.2058 0.0025 1.0000 38.000 0.9100 0.51178 0.51062 -0.2079 0.0024 1.0000 38.500 0.9074 0.51747 0.51633 -0.2099 0.0023 1.0000 40.000 0.9000 0.53691 0.53583 -0.2160 0.0022 1.0000 40.500 0.8975 0.54335 0.54230 -0.2180 0.0022 1.0000 41.000 0.8946 0.54952 0.54849 -0.2199 0.0021 1.0000 41.500 0.8914 0.55540 0.55440 -0.2218 0.0020 1.0000 42.000 0.8878 0.56087 0.55989 -0.2237 0.0018 1.0000 42.500 0.8839 0.56611 0.56516 -0.2256 0.0017 1.0000 43.000 0.8797 0.57103 0.57010 -0.2275 0.0015 1.0000 43.500 0.8752 0.57575 0.57484 -0.2294 0.0014 1.0000 44.000 0.8704 0.58009 0.57921 -0.2313 0.0013 1.0000 44.500 0.8653 0.58409 0.58324 -0.2333 0.0012 1.0000 45.000 0.8597 0.58769 0.58686 -0.2352 0.0011 1.0000 47.000 0.8374 0.60451 0.60377 -0.2422 0.0010 1.0000 47.500 0.8315 0.60818 0.60746 -0.2438 0.0010 1.0000 48.000 0.8253 0.61151 0.61081 -0.2455 0.0010 1.0000 48.500 0.8189 0.61454 0.61387 -0.2471 0.0009 1.0000 49.000 0.8123 0.61723 0.61658 -0.2487 0.0009 1.0000 49.500 0.8054 0.61972 0.61909 -0.2503 0.0008 1.0000 50.000 0.7983 0.62186 0.62126 -0.2519 0.0007 1.0000 50.500 0.7910 0.62378 0.62320 -0.2535 0.0006 1.0000 51.000 0.7834 0.62537 0.62482 -0.2551 0.0005 1.0000 51.500 0.7757 0.62660 0.62607 -0.2567 0.0004 1.0000 52.000 0.7677 0.62745 0.62693 -0.2582 0.0004 1.0000 52.500 0.7594 0.62790 0.62741 -0.2598 0.0003 1.0000 54.000 0.7348 0.63057 0.63014 -0.2640 0.0003 1.0000 54.500 0.7265 0.63101 0.63060 -0.2653 0.0002 1.0000 55.000 0.7178 0.63089 0.63050 -0.2666 0.0002 1.0000 55.500 0.7089 0.63042 0.63005 -0.2679 0.0002 1.0000 56.000 0.6998 0.62949 0.62914 -0.2692 0.0001 1.0000 57.500 0.6723 0.62668 0.62639 -0.2729 0.0001 1.0000 58.000 0.6629 0.62527 0.62500 -0.2740 0.0001 1.0000 58.500 0.6533 0.62353 0.62328 -0.2752 0.0000 1.0000 59.000 0.6436 0.62139 0.62116 -0.2763 0.0000 1.0000 59.500 0.6338 0.61895 0.61873 -0.2774 0.0000 1.0000