XFOIL Version 6.96 Calculated polar for: USA 35 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.8659 0.03494 0.03127 -0.1314 0.9185 0.0261 -15.250 -0.8807 0.02924 0.02527 -0.1381 0.8969 0.0261 -15.000 -0.8803 0.02732 0.02317 -0.1378 0.8774 0.0262 -14.750 -0.8712 0.02600 0.02169 -0.1371 0.8606 0.0263 -14.500 -0.8570 0.02488 0.02043 -0.1367 0.8468 0.0264 -14.250 -0.8405 0.02390 0.01931 -0.1362 0.8345 0.0265 -14.000 -0.8221 0.02301 0.01831 -0.1358 0.8244 0.0267 -13.750 -0.8024 0.02220 0.01740 -0.1354 0.8157 0.0268 -13.500 -0.7814 0.02145 0.01655 -0.1350 0.8073 0.0269 -13.250 -0.7598 0.02077 0.01576 -0.1346 0.7983 0.0271 -13.000 -0.7373 0.02012 0.01501 -0.1342 0.7907 0.0272 -12.750 -0.7141 0.01951 0.01432 -0.1339 0.7823 0.0273 -12.250 -0.6660 0.01841 0.01305 -0.1332 0.7682 0.0276 -12.000 -0.6412 0.01792 0.01247 -0.1329 0.7605 0.0277 -11.750 -0.6162 0.01747 0.01192 -0.1326 0.7528 0.0278 -11.500 -0.5905 0.01702 0.01140 -0.1324 0.7461 0.0279 -11.250 -0.5654 0.01650 0.01082 -0.1321 0.7379 0.0282 -11.000 -0.5401 0.01604 0.01028 -0.1318 0.7300 0.0284 -10.750 -0.5138 0.01563 0.00982 -0.1316 0.7220 0.0287 -10.500 -0.4874 0.01529 0.00941 -0.1314 0.7124 0.0290 -10.250 -0.4606 0.01496 0.00902 -0.1312 0.7031 0.0292 -10.000 -0.4340 0.01466 0.00865 -0.1309 0.6914 0.0294 -9.750 -0.4069 0.01437 0.00829 -0.1307 0.6803 0.0297 -9.500 -0.3800 0.01412 0.00795 -0.1305 0.6681 0.0300 -9.250 -0.3526 0.01385 0.00762 -0.1303 0.6560 0.0302 -9.000 -0.3255 0.01362 0.00730 -0.1301 0.6434 0.0305 -8.750 -0.2983 0.01342 0.00700 -0.1299 0.6291 0.0308 -8.500 -0.2707 0.01321 0.00672 -0.1297 0.6154 0.0310 -8.250 -0.2433 0.01303 0.00645 -0.1295 0.6022 0.0313 -7.750 -0.1882 0.01263 0.00591 -0.1292 0.5784 0.0320 -7.250 -0.1324 0.01230 0.00547 -0.1289 0.5596 0.0328 -7.000 -0.1044 0.01215 0.00528 -0.1288 0.5512 0.0333 -6.750 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0.01040 0.00314 -0.1287 0.4668 0.0547 -1.500 0.5270 0.01040 0.00312 -0.1287 0.4637 0.0564 -1.250 0.5561 0.01036 0.00310 -0.1288 0.4618 0.0582 -1.000 0.5850 0.01032 0.00308 -0.1289 0.4593 0.0604 -0.750 0.6138 0.01030 0.00307 -0.1289 0.4564 0.0625 -0.500 0.6423 0.01029 0.00306 -0.1289 0.4528 0.0649 -0.250 0.6705 0.01031 0.00307 -0.1289 0.4488 0.0677 0.000 0.6984 0.01033 0.00308 -0.1288 0.4446 0.0708 0.250 0.7271 0.01032 0.00309 -0.1289 0.4416 0.0744 0.500 0.7556 0.01031 0.00310 -0.1289 0.4380 0.0785 0.750 0.7837 0.01032 0.00312 -0.1289 0.4336 0.0837 1.250 0.8390 0.01037 0.00320 -0.1287 0.4248 0.1026 1.500 0.8670 0.01032 0.00324 -0.1287 0.4201 0.1314 1.750 0.8943 0.01029 0.00331 -0.1287 0.4140 0.1753 2.000 0.9210 0.01034 0.00340 -0.1285 0.4071 0.2059 2.250 0.9476 0.01038 0.00349 -0.1283 0.3975 0.2379 2.500 0.9733 0.01046 0.00360 -0.1279 0.3868 0.2761 2.750 0.9982 0.01054 0.00376 -0.1275 0.3750 0.3338 3.000 1.0239 0.01049 0.00393 -0.1273 0.3660 0.4405 3.250 1.0486 0.01048 0.00413 -0.1269 0.3575 0.5483 3.500 1.0735 0.01035 0.00434 -0.1265 0.3496 0.6964 3.750 1.0899 0.01014 0.00463 -0.1241 0.3412 0.9024 4.000 1.1176 0.01023 0.00477 -0.1240 0.3345 1.0000 4.250 1.1415 0.01046 0.00494 -0.1233 0.3283 1.0000 4.500 1.1652 0.01069 0.00513 -0.1226 0.3233 1.0000 4.750 1.1892 0.01087 0.00528 -0.1219 0.3197 1.0000 5.000 1.2118 0.01107 0.00546 -0.1210 0.3156 1.0000 5.250 1.2333 0.01134 0.00568 -0.1199 0.3107 1.0000 5.500 1.2550 0.01161 0.00591 -0.1189 0.3057 1.0000 5.750 1.2780 0.01183 0.00612 -0.1181 0.3022 1.0000 6.000 1.3004 0.01208 0.00635 -0.1173 0.2985 1.0000 6.250 1.3223 0.01236 0.00661 -0.1164 0.2949 1.0000 6.500 1.3432 0.01269 0.00691 -0.1154 0.2909 1.0000 6.750 1.3657 0.01295 0.00717 -0.1146 0.2881 1.0000 7.000 1.3882 0.01322 0.00744 -0.1139 0.2851 1.0000 7.250 1.4098 0.01353 0.00774 -0.1131 0.2821 1.0000 7.500 1.4309 0.01387 0.00807 -0.1122 0.2791 1.0000 7.750 1.4509 0.01426 0.00844 -0.1112 0.2758 1.0000 8.000 1.4713 0.01464 0.00882 -0.1103 0.2730 1.0000 8.250 1.4930 0.01497 0.00916 -0.1095 0.2706 1.0000 8.500 1.5135 0.01536 0.00955 -0.1087 0.2673 1.0000 8.750 1.5326 0.01582 0.01000 -0.1077 0.2635 1.0000 9.000 1.5506 0.01635 0.01052 -0.1066 0.2596 1.0000 9.250 1.5695 0.01684 0.01101 -0.1056 0.2567 1.0000 9.500 1.5891 0.01730 0.01149 -0.1048 0.2537 1.0000 9.750 1.6072 0.01786 0.01205 -0.1038 0.2498 1.0000 10.000 1.6232 0.01854 0.01272 -0.1026 0.2455 1.0000 10.250 1.6397 0.01921 0.01339 -0.1016 0.2417 1.0000 10.500 1.6567 0.01987 0.01407 -0.1006 0.2374 1.0000 10.750 1.6711 0.02070 0.01489 -0.0994 0.2320 1.0000 11.000 1.6846 0.02161 0.01579 -0.0982 0.2270 1.0000 11.250 1.6979 0.02255 0.01673 -0.0970 0.2207 1.0000 11.500 1.7079 0.02373 0.01790 -0.0955 0.2138 1.0000 11.750 1.7169 0.02502 0.01917 -0.0941 0.2055 1.0000 12.000 1.7237 0.02651 0.02063 -0.0925 0.1972 1.0000 12.250 1.7272 0.02826 0.02235 -0.0907 0.1882 1.0000 12.500 1.7307 0.03010 0.02418 -0.0891 0.1803 1.0000 12.750 1.7348 0.03196 0.02604 -0.0877 0.1746 1.0000 13.000 1.7403 0.03374 0.02782 -0.0865 0.1698 1.0000 13.250 1.7430 0.03581 0.02991 -0.0852 0.1656 1.0000 13.500 1.7490 0.03766 0.03179 -0.0842 0.1627 1.0000 13.750 1.7554 0.03949 0.03366 -0.0833 0.1602 1.0000 14.000 1.7594 0.04160 0.03580 -0.0824 0.1578 1.0000 14.250 1.7611 0.04395 0.03818 -0.0814 0.1553 1.0000 14.500 1.7634 0.04628 0.04056 -0.0806 0.1529 1.0000 14.750 1.7688 0.04837 0.04270 -0.0800 0.1514 1.0000 15.000 1.7728 0.05063 0.04501 -0.0794 0.1500 1.0000 15.250 1.7763 0.05293 0.04737 -0.0788 0.1484 1.0000 15.500 1.7767 0.05560 0.05008 -0.0782 0.1467 1.0000 15.750 1.7761 0.05841 0.05294 -0.0776 0.1451 1.0000 16.000 1.7749 0.06129 0.05587 -0.0771 0.1432 1.0000 16.250 1.7731 0.06430 0.05894 -0.0767 0.1415 1.0000 16.500 1.7764 0.06670 0.06140 -0.0764 0.1403 1.0000 16.750 1.7773 0.06943 0.06419 -0.0761 0.1391 1.0000 17.000 1.7784 0.07211 0.06693 -0.0758 0.1377 1.0000 17.250 1.7769 0.07513 0.07001 -0.0756 0.1363 1.0000 17.500 1.7759 0.07809 0.07302 -0.0754 0.1348 1.0000 17.750 1.7719 0.08141 0.07640 -0.0752 0.1334 1.0000 18.000 1.7696 0.08452 0.07955 -0.0751 0.1320 1.0000 18.250 1.7663 0.08783 0.08292 -0.0751 0.1308 1.0000 18.500 1.7694 0.09033 0.08549 -0.0752 0.1297 1.0000 18.750 1.7686 0.09333 0.08855 -0.0753 0.1282 1.0000 19.000 1.7681 0.09628 0.09155 -0.0754 0.1267 1.0000 19.250 1.7675 0.09922 0.09454 -0.0756 0.1252 1.0000