XFOIL Version 6.96 Calculated polar for: E392 (10.15%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.3303 0.08985 0.08642 -0.0409 1.0000 0.0162 -8.500 -0.3270 0.08762 0.08423 -0.0404 1.0000 0.0156 -8.250 -0.3279 0.08469 0.08136 -0.0406 1.0000 0.0151 -8.000 -0.3317 0.08169 0.07844 -0.0408 1.0000 0.0146 -7.750 -0.3341 0.07818 0.07501 -0.0421 0.9964 0.0142 -7.500 -0.3225 0.07195 0.06878 -0.0499 0.9785 0.0134 -7.250 -0.3070 0.05729 0.05408 -0.0703 0.9548 0.0118 -7.000 -0.2866 0.04841 0.04499 -0.0818 0.9356 0.0116 -6.750 -0.2675 0.03952 0.03567 -0.0904 0.9172 0.0114 -6.250 -0.2254 0.02734 0.02204 -0.0975 0.8840 0.0120 -6.000 -0.2007 0.02541 0.01982 -0.0985 0.8691 0.0128 -5.750 -0.1755 0.02332 0.01732 -0.0990 0.8548 0.0134 -5.500 -0.1501 0.02096 0.01443 -0.0990 0.8413 0.0134 -5.250 -0.1243 0.01921 0.01227 -0.0988 0.8283 0.0137 -5.000 -0.0983 0.01783 0.01058 -0.0985 0.8159 0.0141 -4.750 -0.0720 0.01670 0.00920 -0.0982 0.8042 0.0145 -4.500 -0.0457 0.01575 0.00803 -0.0979 0.7933 0.0152 -4.000 0.0074 0.01430 0.00628 -0.0975 0.7726 0.0177 -3.750 0.0344 0.01387 0.00574 -0.0974 0.7632 0.0207 -3.500 0.0615 0.01333 0.00505 -0.0972 0.7544 0.0234 -3.250 0.0889 0.01286 0.00449 -0.0971 0.7454 0.0302 -3.000 0.1163 0.01241 0.00405 -0.0971 0.7374 0.0530 -2.750 0.1434 0.01200 0.00378 -0.0972 0.7291 0.0968 -2.500 0.1705 0.01157 0.00356 -0.0973 0.7217 0.1649 -2.250 0.1977 0.01123 0.00337 -0.0974 0.7141 0.2334 -2.000 0.2248 0.01088 0.00324 -0.0975 0.7073 0.3195 -1.750 0.2515 0.01056 0.00317 -0.0974 0.7001 0.4188 -1.500 0.2781 0.01034 0.00313 -0.0972 0.6939 0.5077 -1.250 0.3046 0.01017 0.00312 -0.0969 0.6869 0.5776 -1.000 0.3306 0.01006 0.00309 -0.0963 0.6811 0.6377 -0.750 0.3561 0.00993 0.00310 -0.0957 0.6745 0.6956 -0.500 0.3806 0.00983 0.00310 -0.0946 0.6686 0.7538 -0.250 0.4036 0.00973 0.00310 -0.0932 0.6629 0.8141 0.000 0.4268 0.00962 0.00306 -0.0917 0.6568 0.8834 0.250 0.4641 0.00952 0.00293 -0.0934 0.6515 0.9897 0.500 0.4925 0.00961 0.00294 -0.0936 0.6452 1.0000 0.750 0.5204 0.00972 0.00295 -0.0937 0.6396 1.0000 1.000 0.5483 0.00983 0.00299 -0.0938 0.6342 1.0000 1.250 0.5761 0.00994 0.00304 -0.0938 0.6281 1.0000 1.500 0.6039 0.01007 0.00309 -0.0939 0.6230 1.0000 1.750 0.6317 0.01019 0.00319 -0.0939 0.6170 1.0000 2.000 0.6593 0.01031 0.00328 -0.0939 0.6113 1.0000 2.250 0.6870 0.01045 0.00337 -0.0939 0.6061 1.0000 2.500 0.7145 0.01058 0.00352 -0.0939 0.5997 1.0000 2.750 0.7421 0.01072 0.00362 -0.0939 0.5942 1.0000 3.000 0.7694 0.01086 0.00377 -0.0939 0.5877 1.0000 3.250 0.7967 0.01099 0.00391 -0.0938 0.5811 1.0000 3.500 0.8238 0.01113 0.00408 -0.0937 0.5736 1.0000 3.750 0.8507 0.01127 0.00421 -0.0936 0.5656 1.0000 4.000 0.8775 0.01141 0.00439 -0.0934 0.5567 1.0000 4.250 0.9042 0.01156 0.00456 -0.0932 0.5481 1.0000 4.500 0.9307 0.01170 0.00474 -0.0930 0.5381 1.0000 4.750 0.9570 0.01185 0.00494 -0.0927 0.5274 1.0000 5.000 0.9830 0.01201 0.00513 -0.0924 0.5161 1.0000 5.250 1.0088 0.01219 0.00536 -0.0921 0.5038 1.0000 5.500 1.0343 0.01237 0.00558 -0.0917 0.4902 1.0000 5.750 1.0594 0.01258 0.00583 -0.0912 0.4744 1.0000 6.000 1.0840 0.01281 0.00609 -0.0907 0.4553 1.0000 6.250 1.1070 0.01312 0.00638 -0.0899 0.4269 1.0000 6.500 1.1276 0.01359 0.00671 -0.0887 0.3837 1.0000 6.750 1.1439 0.01441 0.00720 -0.0870 0.3204 1.0000 7.000 1.1583 0.01546 0.00792 -0.0853 0.2584 1.0000 7.250 1.1730 0.01652 0.00873 -0.0836 0.2091 1.0000 7.500 1.1868 0.01765 0.00963 -0.0819 0.1613 1.0000 7.750 1.1996 0.01882 0.01055 -0.0801 0.1196 1.0000 8.000 1.2124 0.01994 0.01149 -0.0782 0.0871 1.0000 8.250 1.2256 0.02098 0.01242 -0.0764 0.0643 1.0000 8.500 1.2368 0.02209 0.01345 -0.0743 0.0441 1.0000 8.750 1.2456 0.02321 0.01454 -0.0718 0.0311 1.0000 9.000 1.2534 0.02435 0.01568 -0.0692 0.0248 1.0000 9.250 1.2628 0.02542 0.01688 -0.0670 0.0219 1.0000 9.500 1.2701 0.02667 0.01819 -0.0647 0.0199 1.0000 9.750 1.2764 0.02806 0.01967 -0.0625 0.0185 1.0000 10.000 1.2840 0.02940 0.02114 -0.0607 0.0174 1.0000 10.250 1.2906 0.03089 0.02275 -0.0590 0.0165 1.0000 10.500 1.2962 0.03256 0.02454 -0.0574 0.0158 1.0000 10.750 1.3006 0.03441 0.02651 -0.0559 0.0153 1.0000 11.000 1.3040 0.03645 0.02866 -0.0546 0.0149 1.0000 11.250 1.3058 0.03873 0.03107 -0.0535 0.0145 1.0000 11.500 1.3056 0.04132 0.03377 -0.0524 0.0141 1.0000 11.750 1.3062 0.04393 0.03648 -0.0515 0.0138 1.0000 12.000 1.3097 0.04632 0.03901 -0.0507 0.0136 1.0000 12.250 1.3134 0.04878 0.04160 -0.0500 0.0134 1.0000 12.500 1.3171 0.05127 0.04423 -0.0494 0.0132 1.0000 12.750 1.3211 0.05381 0.04693 -0.0489 0.0128 1.0000 13.000 1.3246 0.05645 0.04971 -0.0485 0.0124 1.0000 13.250 1.3275 0.05921 0.05263 -0.0482 0.0120 1.0000 13.500 1.3296 0.06212 0.05569 -0.0481 0.0116 1.0000 13.750 1.3310 0.06520 0.05895 -0.0481 0.0114 1.0000 14.000 1.3316 0.06846 0.06237 -0.0482 0.0111 1.0000 14.250 1.3314 0.07194 0.06601 -0.0484 0.0109 1.0000 14.500 1.3300 0.07566 0.06989 -0.0489 0.0108 1.0000 14.750 1.3272 0.07965 0.07405 -0.0497 0.0106 1.0000 15.000 1.3235 0.08393 0.07851 -0.0507 0.0105 1.0000 15.250 1.3183 0.08855 0.08331 -0.0519 0.0103 1.0000 15.500 1.3117 0.09353 0.08847 -0.0536 0.0102 1.0000 15.750 1.3035 0.09893 0.09405 -0.0556 0.0101 1.0000 16.000 1.2938 0.10477 0.10010 -0.0580 0.0101 1.0000 16.250 1.2828 0.11108 0.10660 -0.0610 0.0100 1.0000 16.500 1.2699 0.11796 0.11368 -0.0645 0.0099 1.0000 16.750 1.2562 0.12534 0.12127 -0.0686 0.0098 1.0000 17.000 1.2422 0.13314 0.12926 -0.0733 0.0098 1.0000 17.250 1.2281 0.14137 0.13768 -0.0786 0.0098 1.0000 17.500 1.2138 0.15014 0.14663 -0.0844 0.0098 1.0000 17.750 1.1989 0.15962 0.15630 -0.0908 0.0099 1.0000 18.000 1.1764 0.17261 0.16953 -0.0996 0.0101 1.0000