XFOIL Version 6.96 Calculated polar for: GOE 123 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3027 0.10501 0.10028 -0.0282 1.0000 0.0344 -7.750 -0.3167 0.10501 0.10041 -0.0258 1.0000 0.0345 -7.500 -0.3270 0.10473 0.10021 -0.0249 1.0000 0.0347 -7.250 -0.3194 0.10334 0.09884 -0.0302 0.9966 0.0349 -7.000 -0.3035 0.09765 0.09317 -0.0324 0.9927 0.0353 -6.750 -0.2923 0.09227 0.08780 -0.0305 0.9901 0.0363 -6.500 -0.2723 0.08820 0.08370 -0.0339 0.9860 0.0376 -6.250 -0.2512 0.08456 0.08004 -0.0383 0.9800 0.0392 -6.000 -0.2259 0.08088 0.07633 -0.0442 0.9747 0.0415 -5.750 -0.1669 0.07869 0.07389 -0.0637 0.9671 0.0457 -5.500 -0.1501 0.07378 0.06900 -0.0654 0.9615 0.0463 -5.250 -0.1352 0.06937 0.06462 -0.0650 0.9582 0.0477 -5.000 -0.1103 0.06598 0.06118 -0.0684 0.9535 0.0501 -4.500 -0.0277 0.05914 0.05402 -0.0847 0.9442 0.0583 -4.250 -0.0104 0.05599 0.05086 -0.0851 0.9377 0.0601 -4.000 0.0231 0.05294 0.04771 -0.0894 0.9337 0.0637 -3.750 0.0833 0.05195 0.04620 -0.0992 0.9273 0.0696 -3.500 0.0972 0.04721 0.04163 -0.0991 0.9221 0.0718 -3.250 0.1299 0.04447 0.03879 -0.1020 0.9182 0.0762 -3.000 0.1788 0.04424 0.03803 -0.1071 0.9101 0.0831 -2.750 0.2079 0.04025 0.03402 -0.1095 0.9058 0.0842 -2.500 0.2324 0.03768 0.03143 -0.1104 0.8993 0.0859 -2.250 0.2616 0.03568 0.02932 -0.1118 0.8934 0.0894 -2.000 0.3016 0.03408 0.02741 -0.1147 0.8895 0.0993 -1.500 0.3725 0.02850 0.02105 -0.1172 0.8771 0.0560 -1.250 0.4040 0.02684 0.01920 -0.1182 0.8719 0.0544 -1.000 0.4330 0.02542 0.01756 -0.1185 0.8644 0.0532 -0.750 0.4667 0.02388 0.01575 -0.1193 0.8596 0.0522 -0.500 0.4943 0.02281 0.01444 -0.1190 0.8503 0.0536 -0.250 0.5259 0.02160 0.01293 -0.1190 0.8426 0.0553 0.000 0.5538 0.02055 0.01167 -0.1185 0.8318 0.0551 0.250 0.5812 0.01962 0.01056 -0.1179 0.8211 0.0549 0.500 0.6105 0.01872 0.00949 -0.1176 0.8129 0.0551 0.750 0.6367 0.01810 0.00877 -0.1169 0.8023 0.0555 1.000 0.6635 0.01754 0.00814 -0.1163 0.7924 0.0563 1.250 0.6909 0.01698 0.00753 -0.1157 0.7836 0.0574 1.500 0.7163 0.01663 0.00721 -0.1149 0.7718 0.0596 1.750 0.7426 0.01640 0.00697 -0.1142 0.7601 0.0648 2.000 0.7694 0.01618 0.00673 -0.1137 0.7483 0.0727 2.250 0.7964 0.01597 0.00648 -0.1131 0.7358 0.0826 2.500 0.8234 0.01580 0.00642 -0.1125 0.7221 0.1129 2.750 0.8499 0.01567 0.00632 -0.1120 0.7071 0.1725 3.000 0.8720 0.01427 0.00632 -0.1106 0.6909 1.0000 3.250 0.8977 0.01438 0.00633 -0.1099 0.6725 1.0000 3.500 0.9232 0.01449 0.00634 -0.1091 0.6520 1.0000 3.750 0.9485 0.01463 0.00635 -0.1082 0.6285 1.0000 4.000 0.9734 0.01480 0.00641 -0.1073 0.6027 1.0000 4.250 0.9980 0.01504 0.00652 -0.1065 0.5759 1.0000 4.500 1.0224 0.01533 0.00669 -0.1056 0.5500 1.0000 5.000 1.0701 0.01609 0.00724 -0.1039 0.5005 1.0000 5.250 1.0934 0.01654 0.00759 -0.1030 0.4754 1.0000 5.500 1.1163 0.01701 0.00798 -0.1021 0.4509 1.0000 5.750 1.1391 0.01750 0.00842 -0.1012 0.4275 1.0000 6.000 1.1615 0.01801 0.00891 -0.1003 0.4060 1.0000 6.250 1.1840 0.01854 0.00941 -0.0994 0.3876 1.0000 6.500 1.2065 0.01907 0.00996 -0.0986 0.3702 1.0000 6.750 1.2283 0.01964 0.01054 -0.0977 0.3514 1.0000 7.000 1.2493 0.02024 0.01118 -0.0966 0.3317 1.0000 7.250 1.2695 0.02090 0.01181 -0.0955 0.3120 1.0000 7.500 1.2893 0.02153 0.01249 -0.0944 0.2886 1.0000 7.750 1.3074 0.02225 0.01319 -0.0930 0.2600 1.0000 8.000 1.3248 0.02304 0.01397 -0.0916 0.2268 1.0000 8.250 1.3394 0.02407 0.01484 -0.0900 0.1826 1.0000 8.500 1.3490 0.02568 0.01605 -0.0878 0.1149 1.0000 8.750 1.3540 0.02784 0.01780 -0.0851 0.0723 1.0000 9.000 1.3626 0.02959 0.01945 -0.0827 0.0489 1.0000 9.250 1.3703 0.03125 0.02112 -0.0802 0.0412 1.0000 9.500 1.3734 0.03303 0.02295 -0.0772 0.0374 1.0000 9.750 1.3770 0.03475 0.02488 -0.0743 0.0346 1.0000 10.000 1.3801 0.03654 0.02686 -0.0716 0.0319 1.0000 10.250 1.3807 0.03859 0.02905 -0.0691 0.0298 1.0000 10.500 1.3784 0.04096 0.03157 -0.0665 0.0285 1.0000 10.750 1.3734 0.04371 0.03443 -0.0640 0.0275 1.0000 11.000 1.3742 0.04610 0.03697 -0.0619 0.0267 1.0000 11.250 1.3774 0.04837 0.03943 -0.0602 0.0256 1.0000 11.500 1.3804 0.05074 0.04199 -0.0586 0.0243 1.0000 11.750 1.3828 0.05324 0.04465 -0.0572 0.0230 1.0000 12.000 1.3848 0.05587 0.04743 -0.0559 0.0220 1.0000 12.250 1.3872 0.05861 0.05034 -0.0545 0.0213 1.0000 12.500 1.3893 0.06147 0.05334 -0.0533 0.0207 1.0000 12.750 1.3910 0.06450 0.05652 -0.0522 0.0201 1.0000 13.000 1.3924 0.06777 0.05993 -0.0511 0.0197 1.0000 13.250 1.3928 0.07157 0.06389 -0.0499 0.0191 1.0000 13.500 1.3873 0.07557 0.06813 -0.0495 0.0188 1.0000 13.750 1.3788 0.07979 0.07264 -0.0497 0.0185 1.0000 14.000 1.3686 0.08441 0.07755 -0.0503 0.0183 1.0000 14.250 1.3569 0.08946 0.08287 -0.0515 0.0180 1.0000 14.500 1.3438 0.09494 0.08862 -0.0532 0.0178 1.0000 14.750 1.3297 0.10093 0.09485 -0.0556 0.0177 1.0000 15.000 1.3150 0.10743 0.10160 -0.0586 0.0176 1.0000 15.250 1.2995 0.11448 0.10888 -0.0624 0.0175 1.0000 15.500 1.2835 0.12205 0.11666 -0.0667 0.0176 1.0000 15.750 1.2670 0.13024 0.12506 -0.0717 0.0177 1.0000 16.000 1.2504 0.13903 0.13403 -0.0774 0.0178 1.0000