XFOIL Version 6.96 Calculated polar for: FX 61-168 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.3622 0.11434 0.11212 -0.0454 1.0000 0.0178 -11.750 -0.3703 0.10710 0.10492 -0.0487 1.0000 0.0190 -9.250 -0.4812 0.03413 0.03008 -0.0975 0.9140 0.0145 -9.000 -0.4349 0.02554 0.02057 -0.1068 0.8933 0.0127 -8.750 -0.3779 0.02229 0.01677 -0.1141 0.8581 0.0128 -8.500 -0.3473 0.02134 0.01551 -0.1155 0.8182 0.0134 -8.250 -0.3259 0.02050 0.01439 -0.1147 0.7898 0.0139 -8.000 -0.3059 0.01996 0.01360 -0.1137 0.7684 0.0147 -7.750 -0.2855 0.01939 0.01280 -0.1126 0.7516 0.0151 -7.500 -0.2651 0.01788 0.01119 -0.1111 0.7387 0.0156 -7.250 -0.2471 0.01707 0.01034 -0.1098 0.7277 0.0164 -7.000 -0.2281 0.01648 0.00965 -0.1087 0.7184 0.0168 -6.750 -0.2084 0.01595 0.00906 -0.1078 0.7099 0.0178 -6.500 -0.1881 0.01542 0.00844 -0.1070 0.7028 0.0186 -6.250 -0.1654 0.01507 0.00801 -0.1065 0.6958 0.0198 -5.750 -0.1242 0.01367 0.00651 -0.1056 0.6841 0.0233 -5.500 -0.0993 0.01329 0.00604 -0.1055 0.6789 0.0254 -5.250 -0.0742 0.01274 0.00542 -0.1057 0.6744 0.0298 -5.000 -0.0480 0.01229 0.00498 -0.1059 0.6698 0.0383 -4.750 -0.0220 0.01143 0.00439 -0.1067 0.6653 0.1018 -4.500 0.0091 0.00930 0.00342 -0.1106 0.6610 0.3983 -4.250 0.0417 0.00877 0.00327 -0.1124 0.6569 0.5195 -4.000 0.0717 0.00873 0.00331 -0.1130 0.6527 0.5625 -3.750 0.1011 0.00883 0.00340 -0.1132 0.6486 0.5874 -3.500 0.1313 0.00904 0.00350 -0.1137 0.6449 0.6067 -3.250 0.1602 0.00934 0.00378 -0.1136 0.6415 0.6229 -3.000 0.1882 0.00961 0.00405 -0.1134 0.6379 0.6333 -2.750 0.2169 0.00975 0.00414 -0.1135 0.6343 0.6395 -2.500 0.2457 0.00986 0.00420 -0.1137 0.6311 0.6429 -2.250 0.2755 0.00999 0.00423 -0.1141 0.6278 0.6469 -2.000 0.3055 0.01001 0.00418 -0.1147 0.6242 0.6517 -1.750 0.3333 0.01005 0.00422 -0.1147 0.6202 0.6542 -1.500 0.3616 0.01013 0.00428 -0.1148 0.6167 0.6570 -1.250 0.3912 0.01026 0.00433 -0.1152 0.6136 0.6602 -1.000 0.4205 0.01032 0.00436 -0.1156 0.6104 0.6644 -0.750 0.4496 0.01036 0.00437 -0.1159 0.6070 0.6680 -0.500 0.4775 0.01043 0.00445 -0.1159 0.6038 0.6705 -0.250 0.5060 0.01053 0.00453 -0.1161 0.6008 0.6734 0.000 0.5356 0.01068 0.00461 -0.1166 0.5978 0.6768 0.250 0.5647 0.01071 0.00464 -0.1170 0.5945 0.6805 0.500 0.5934 0.01071 0.00464 -0.1173 0.5906 0.6831 0.750 0.6212 0.01074 0.00468 -0.1173 0.5869 0.6852 1.000 0.6497 0.01083 0.00474 -0.1175 0.5834 0.6873 1.250 0.6780 0.01089 0.00481 -0.1177 0.5799 0.6897 1.500 0.7063 0.01092 0.00486 -0.1180 0.5760 0.6926 1.750 0.7354 0.01096 0.00488 -0.1184 0.5723 0.6955 2.000 0.7648 0.01101 0.00490 -0.1189 0.5690 0.6978 2.250 0.7930 0.01107 0.00498 -0.1191 0.5656 0.6996 2.500 0.8201 0.01109 0.00506 -0.1190 0.5616 0.7016 2.750 0.8476 0.01112 0.00511 -0.1191 0.5571 0.7038 3.000 0.8759 0.01119 0.00516 -0.1193 0.5528 0.7062 3.250 0.9037 0.01122 0.00524 -0.1195 0.5481 0.7086 3.500 0.9320 0.01125 0.00529 -0.1197 0.5433 0.7110 3.750 0.9600 0.01129 0.00531 -0.1200 0.5386 0.7131 4.000 0.9866 0.01132 0.00540 -0.1198 0.5333 0.7150 4.250 1.0131 0.01134 0.00548 -0.1197 0.5276 0.7169 4.500 1.0402 0.01141 0.00555 -0.1197 0.5223 0.7188 4.750 1.0666 0.01143 0.00564 -0.1195 0.5152 0.7210 5.000 1.0931 0.01148 0.00569 -0.1194 0.5083 0.7235 5.250 1.1201 0.01154 0.00581 -0.1195 0.5011 0.7258 5.500 1.1464 0.01162 0.00587 -0.1194 0.4931 0.7277 5.750 1.1719 0.01165 0.00598 -0.1191 0.4841 0.7295 6.000 1.1967 0.01177 0.00611 -0.1186 0.4760 0.7314 6.250 1.2221 0.01186 0.00628 -0.1184 0.4668 0.7334 6.500 1.2469 0.01200 0.00644 -0.1180 0.4568 0.7355 6.750 1.2709 0.01218 0.00662 -0.1175 0.4453 0.7378 7.000 1.2945 0.01239 0.00682 -0.1169 0.4328 0.7401 7.250 1.3177 0.01263 0.00705 -0.1163 0.4188 0.7421 7.500 1.3385 0.01291 0.00731 -0.1153 0.4020 0.7438 7.750 1.3585 0.01323 0.00762 -0.1141 0.3828 0.7458 8.000 1.3765 0.01364 0.00798 -0.1125 0.3621 0.7478 8.250 1.3928 0.01413 0.00841 -0.1108 0.3401 0.7498 8.500 1.4069 0.01467 0.00886 -0.1086 0.3152 0.7519 8.750 1.4176 0.01527 0.00936 -0.1059 0.2897 0.7542 9.000 1.4271 0.01600 0.00998 -0.1031 0.2641 0.7565 9.250 1.4343 0.01682 0.01069 -0.1000 0.2382 0.7585 9.500 1.4403 0.01770 0.01148 -0.0969 0.2141 0.7604 9.750 1.4446 0.01869 0.01239 -0.0936 0.1912 0.7624 10.000 1.4475 0.01979 0.01343 -0.0903 0.1717 0.7646 10.250 1.4501 0.02099 0.01456 -0.0873 0.1542 0.7671 10.500 1.4524 0.02230 0.01583 -0.0845 0.1374 0.7696 10.750 1.4529 0.02384 0.01731 -0.0818 0.1213 0.7719 11.000 1.4528 0.02552 0.01896 -0.0794 0.1061 0.7740 11.250 1.4525 0.02737 0.02080 -0.0773 0.0930 0.7762 11.500 1.4520 0.02941 0.02283 -0.0755 0.0803 0.7784 11.750 1.4504 0.03170 0.02509 -0.0740 0.0677 0.7808 12.000 1.4487 0.03415 0.02752 -0.0727 0.0576 0.7833 12.250 1.4486 0.03658 0.02997 -0.0717 0.0491 0.7859 12.500 1.4464 0.03931 0.03270 -0.0709 0.0403 0.7884 13.000 1.4434 0.04483 0.03828 -0.0696 0.0282 0.7932 13.250 1.4430 0.04762 0.04112 -0.0692 0.0233 0.7958 13.500 1.4405 0.05073 0.04426 -0.0689 0.0183 0.7984 13.750 1.4382 0.05394 0.04750 -0.0687 0.0140 0.8011 14.000 1.4346 0.05738 0.05099 -0.0687 0.0102 0.8036 14.250 1.4321 0.06080 0.05447 -0.0688 0.0079 0.8062 14.500 1.4322 0.06401 0.05779 -0.0691 0.0069 0.8092 14.750 1.4315 0.06744 0.06130 -0.0695 0.0062 0.8124 15.000 1.4304 0.07102 0.06497 -0.0701 0.0057 0.8159 15.250 1.4305 0.07450 0.06858 -0.0707 0.0055 0.8194 15.500 1.4302 0.07813 0.07234 -0.0715 0.0052 0.8232 15.750 1.4295 0.08190 0.07625 -0.0724 0.0050 0.8275 16.000 1.4284 0.08584 0.08031 -0.0734 0.0049 0.8319 16.250 1.4260 0.09001 0.08460 -0.0746 0.0047 0.8363 16.500 1.4231 0.09436 0.08908 -0.0760 0.0046 0.8416 17.000 1.4144 0.10379 0.09879 -0.0793 0.0044 0.8540 17.250 1.4086 0.10882 0.10397 -0.0812 0.0043 0.8619 17.500 1.4003 0.11429 0.10959 -0.0833 0.0042 0.8715 17.750 1.3926 0.11949 0.11496 -0.0853 0.0041 0.8873