XFOIL Version 6.96 Calculated polar for: GOE 776 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2945 0.07811 0.07350 -0.0449 1.0000 0.0900 -19.500 -1.2920 0.07549 0.07082 -0.0455 1.0000 0.0914 -19.250 -1.3006 0.07166 0.06694 -0.0463 1.0000 0.0931 -19.000 -1.3073 0.06803 0.06328 -0.0469 1.0000 0.0949 -18.750 -1.3079 0.06515 0.06035 -0.0474 1.0000 0.0966 -18.500 -1.3075 0.06237 0.05752 -0.0479 1.0000 0.0982 -18.250 -1.3020 0.06018 0.05527 -0.0482 1.0000 0.0994 -18.000 -1.3078 0.05684 0.05190 -0.0485 1.0000 0.1013 -17.750 -1.3104 0.05385 0.04887 -0.0488 1.0000 0.1030 -17.500 -1.3082 0.05140 0.04639 -0.0489 1.0000 0.1048 -17.250 -1.3042 0.04916 0.04410 -0.0490 1.0000 0.1065 -17.000 -1.2963 0.04733 0.04221 -0.0491 1.0000 0.1079 -16.750 -1.2972 0.04470 0.03955 -0.0489 1.0000 0.1100 -16.500 -1.2956 0.04233 0.03716 -0.0488 1.0000 0.1120 -16.250 -1.2900 0.04038 0.03519 -0.0486 1.0000 0.1140 -16.000 -1.2821 0.03866 0.03343 -0.0484 1.0000 0.1158 -15.750 -1.2727 0.03712 0.03184 -0.0481 1.0000 0.1174 -15.500 -1.2696 0.03509 0.02980 -0.0475 1.0000 0.1199 -15.250 -1.2638 0.03333 0.02802 -0.0470 1.0000 0.1222 -15.000 -1.2547 0.03189 0.02657 -0.0464 1.0000 0.1244 -14.750 -1.2438 0.03066 0.02530 -0.0458 1.0000 0.1263 -14.500 -1.2369 0.02920 0.02382 -0.0449 1.0000 0.1287 -14.250 -1.2304 0.02783 0.02245 -0.0437 1.0000 0.1314 -14.000 -1.2232 0.02665 0.02126 -0.0423 1.0000 0.1340 -13.750 -1.2150 0.02574 0.02033 -0.0406 1.0000 0.1363 -13.500 -1.2116 0.02477 0.01934 -0.0383 1.0000 0.1386 -13.250 -1.2140 0.02378 0.01835 -0.0349 1.0000 0.1413 -13.000 -1.2178 0.02303 0.01759 -0.0309 1.0000 0.1438 -12.750 -1.1929 0.02215 0.01670 -0.0320 0.9986 0.1472 -12.500 -1.1686 0.02119 0.01575 -0.0331 0.9966 0.1513 -12.250 -1.1437 0.02027 0.01485 -0.0343 0.9946 0.1556 -12.000 -1.1146 0.01960 0.01417 -0.0358 0.9930 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0.00333 -0.0064 0.5893 0.3891 -2.250 -0.2417 0.00920 0.00329 -0.0060 0.5787 0.3952 -2.000 -0.2178 0.00914 0.00323 -0.0052 0.5687 0.4041 -1.750 -0.1918 0.00910 0.00319 -0.0048 0.5585 0.4119 -1.500 -0.1668 0.00910 0.00316 -0.0041 0.5473 0.4194 -1.250 -0.1414 0.00903 0.00312 -0.0035 0.5378 0.4285 -1.000 -0.1160 0.00906 0.00310 -0.0030 0.5261 0.4359 -0.750 -0.0906 0.00899 0.00307 -0.0024 0.5167 0.4453 -0.500 -0.0657 0.00901 0.00306 -0.0017 0.5054 0.4545 -0.250 -0.0397 0.00899 0.00304 -0.0013 0.4960 0.4632 0.000 -0.0150 0.00898 0.00303 -0.0006 0.4855 0.4733 0.250 0.0111 0.00900 0.00304 -0.0002 0.4760 0.4821 0.500 0.0357 0.00897 0.00304 0.0006 0.4663 0.4930 0.750 0.0615 0.00902 0.00306 0.0011 0.4569 0.5022 1.000 0.0866 0.00899 0.00306 0.0017 0.4484 0.5137 1.250 0.1115 0.00905 0.00309 0.0023 0.4383 0.5235 1.500 0.1372 0.00903 0.00311 0.0029 0.4312 0.5347 1.750 0.1627 0.00907 0.00315 0.0034 0.4224 0.5450 2.000 0.1874 0.00910 0.00319 0.0041 0.4141 0.5554 2.250 0.2135 0.00912 0.00322 0.0045 0.4069 0.5663 2.500 0.2382 0.00918 0.00327 0.0052 0.3983 0.5759 2.750 0.2635 0.00921 0.00332 0.0058 0.3914 0.5867 3.000 0.2896 0.00926 0.00337 0.0062 0.3841 0.5960 3.250 0.3130 0.00932 0.00344 0.0071 0.3755 0.6070 3.500 0.3394 0.00937 0.00350 0.0075 0.3694 0.6165 3.750 0.3639 0.00941 0.00357 0.0082 0.3619 0.6274 4.000 0.3876 0.00952 0.00366 0.0091 0.3536 0.6379 4.250 0.4132 0.00955 0.00372 0.0096 0.3474 0.6480 4.500 0.4369 0.00964 0.00381 0.0104 0.3397 0.6593 4.750 0.4609 0.00973 0.00391 0.0112 0.3325 0.6699 5.000 0.4852 0.00979 0.00400 0.0119 0.3263 0.6818 5.250 0.5073 0.00990 0.00411 0.0131 0.3192 0.6924 5.500 0.5288 0.00997 0.00422 0.0143 0.3131 0.7052 5.750 0.5511 0.01005 0.00432 0.0154 0.3068 0.7168 6.000 0.5715 0.01019 0.00447 0.0169 0.2998 0.7300 6.250 0.5950 0.01030 0.00462 0.0177 0.2942 0.7424 6.500 0.6185 0.01043 0.00478 0.0185 0.2880 0.7561 6.750 0.6399 0.01063 0.00499 0.0196 0.2807 0.7690 7.000 0.6638 0.01077 0.00516 0.0203 0.2753 0.7826 7.250 0.6866 0.01093 0.00537 0.0212 0.2691 0.7962 7.750 0.7314 0.01134 0.00582 0.0230 0.2571 0.8229 8.000 0.7531 0.01158 0.00607 0.0240 0.2507 0.8357 8.250 0.7739 0.01184 0.00636 0.0251 0.2445 0.8493 8.500 0.7966 0.01205 0.00661 0.0259 0.2395 0.8614 8.750 0.8168 0.01236 0.00692 0.0271 0.2334 0.8744 9.000 0.8370 0.01266 0.00725 0.0283 0.2277 0.8864 9.250 0.8582 0.01294 0.00755 0.0292 0.2226 0.8984 9.500 0.8760 0.01332 0.00795 0.0308 0.2168 0.9105 9.750 0.8954 0.01367 0.00831 0.0320 0.2117 0.9222 10.000 0.9137 0.01403 0.00870 0.0334 0.2067 0.9336 10.250 0.9293 0.01452 0.00918 0.0352 0.2010 0.9446 10.500 0.9471 0.01492 0.00959 0.0366 0.1965 0.9555 10.750 0.9654 0.01540 0.01007 0.0378 0.1914 0.9644 11.000 0.9808 0.01602 0.01067 0.0393 0.1858 0.9746 11.250 1.0080 0.01650 0.01116 0.0387 0.1816 0.9795 11.500 1.0333 0.01715 0.01179 0.0381 0.1764 0.9844 11.750 1.0579 0.01786 0.01248 0.0375 0.1714 0.9891 12.000 1.0862 0.01849 0.01311 0.0362 0.1670 0.9914 12.250 1.1132 0.01934 0.01392 0.0348 0.1619 0.9928 12.500 1.1414 0.02007 0.01465 0.0334 0.1577 0.9945 12.750 1.1679 0.02090 0.01547 0.0321 0.1535 0.9964 13.000 1.1909 0.02194 0.01649 0.0310 0.1489 0.9984 13.250 1.2176 0.02277 0.01733 0.0297 0.1456 1.0000 13.500 1.2153 0.02347 0.01805 0.0335 0.1432 1.0000 13.750 1.2140 0.02438 0.01896 0.0368 0.1405 1.0000 14.000 1.2143 0.02550 0.02008 0.0395 0.1375 1.0000 14.250 1.2234 0.02636 0.02096 0.0411 0.1355 1.0000 14.500 1.2322 0.02743 0.02205 0.0424 0.1330 1.0000 14.750 1.2401 0.02870 0.02332 0.0435 0.1303 1.0000 15.000 1.2448 0.03031 0.02493 0.0445 0.1274 1.0000 15.250 1.2566 0.03148 0.02614 0.0451 0.1255 1.0000 15.500 1.2661 0.03288 0.02757 0.0457 0.1233 1.0000 15.750 1.2736 0.03449 0.02919 0.0462 0.1210 1.0000 16.000 1.2782 0.03638 0.03110 0.0467 0.1185 1.0000 16.250 1.2845 0.03821 0.03296 0.0470 0.1166 1.0000 16.500 1.2939 0.03978 0.03457 0.0472 0.1148 1.0000 16.750 1.2995 0.04173 0.03656 0.0474 0.1128 1.0000 17.000 1.3025 0.04396 0.03880 0.0476 0.1108 1.0000 17.250 1.3024 0.04651 0.04137 0.0477 0.1086 1.0000 17.500 1.3082 0.04856 0.04348 0.0477 0.1070 1.0000 17.750 1.3139 0.05062 0.04558 0.0476 0.1053 1.0000 18.000 1.3154 0.05314 0.04814 0.0475 0.1035 1.0000 18.250 1.3137 0.05604 0.05107 0.0472 0.1017 1.0000 18.500 1.3085 0.05929 0.05436 0.0469 0.0998 1.0000 18.750 1.3127 0.06163 0.05676 0.0466 0.0985 1.0000 19.000 1.3147 0.06423 0.05942 0.0462 0.0969 1.0000 19.250 1.3131 0.06725 0.06247 0.0457 0.0952 1.0000