XFOIL Version 6.96 Calculated polar for: GOE 514 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.500 -0.3417 0.11147 0.10848 -0.0975 0.9765 0.0108 -16.250 -0.3562 0.10419 0.10109 -0.1019 0.9754 0.0110 -16.000 -0.3661 0.09790 0.09472 -0.1059 0.9744 0.0111 -15.750 -0.3702 0.09272 0.08947 -0.1096 0.9736 0.0111 -15.500 -0.3772 0.08709 0.08376 -0.1136 0.9728 0.0113 -15.250 -0.3834 0.08307 0.07970 -0.1153 0.9696 0.0112 -15.000 -0.3929 0.07800 0.07456 -0.1184 0.9671 0.0114 -14.750 -0.3996 0.07292 0.06939 -0.1221 0.9650 0.0116 -14.500 -0.4049 0.06799 0.06440 -0.1261 0.9632 0.0117 -14.250 -0.4138 0.06217 0.05849 -0.1312 0.9615 0.0118 -14.000 -0.4218 0.05649 0.05273 -0.1370 0.9598 0.0117 -13.750 -0.4586 0.04917 0.04533 -0.1421 0.9520 0.0118 -13.500 -0.5202 0.03632 0.03214 -0.1558 0.9458 0.0114 -13.250 -0.5432 0.03299 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0.01316 0.00470 -0.0460 0.3877 0.2191 1.500 0.4873 0.01326 0.00483 -0.0445 0.3831 0.2310 1.750 0.5074 0.01337 0.00495 -0.0430 0.3786 0.2412 2.000 0.5272 0.01351 0.00508 -0.0415 0.3743 0.2504 2.250 0.5460 0.01366 0.00523 -0.0399 0.3705 0.2581 2.500 0.5661 0.01381 0.00537 -0.0385 0.3672 0.2649 2.750 0.5866 0.01393 0.00551 -0.0372 0.3639 0.2715 3.000 0.6067 0.01408 0.00565 -0.0359 0.3601 0.2775 3.250 0.6262 0.01426 0.00581 -0.0345 0.3564 0.2827 3.500 0.6448 0.01444 0.00599 -0.0329 0.3527 0.2884 3.750 0.6647 0.01461 0.00617 -0.0316 0.3495 0.2936 4.000 0.6852 0.01476 0.00633 -0.0304 0.3465 0.2981 4.250 0.7050 0.01493 0.00651 -0.0291 0.3435 0.3023 4.500 0.7244 0.01512 0.00671 -0.0278 0.3404 0.3068 4.750 0.7435 0.01533 0.00691 -0.0264 0.3376 0.3120 5.000 0.7618 0.01558 0.00714 -0.0249 0.3346 0.3164 5.250 0.7818 0.01575 0.00736 -0.0238 0.3324 0.3222 5.500 0.8020 0.01594 0.00758 -0.0226 0.3296 0.3289 5.750 0.8218 0.01615 0.00781 -0.0215 0.3266 0.3339 6.000 0.8408 0.01638 0.00806 -0.0202 0.3236 0.3396 6.250 0.8594 0.01663 0.00833 -0.0189 0.3211 0.3461 6.500 0.8769 0.01692 0.00864 -0.0175 0.3184 0.3578 6.750 0.8963 0.01716 0.00892 -0.0164 0.3163 0.3680 7.000 0.9162 0.01736 0.00920 -0.0154 0.3131 0.3840 7.250 0.9360 0.01757 0.00949 -0.0144 0.3112 0.4071 7.750 1.1858 0.01832 0.01163 -0.0586 0.2981 1.0000 8.000 1.2025 0.01863 0.01196 -0.0571 0.2957 1.0000 8.250 1.2185 0.01898 0.01234 -0.0554 0.2934 1.0000 8.500 1.2335 0.01938 0.01273 -0.0537 0.2903 1.0000 8.750 1.2483 0.01981 0.01316 -0.0520 0.2876 1.0000 9.000 1.2623 0.02030 0.01365 -0.0502 0.2848 1.0000 9.250 1.2793 0.02066 0.01405 -0.0489 0.2828 1.0000 9.500 1.2960 0.02106 0.01448 -0.0476 0.2805 1.0000 9.750 1.3123 0.02148 0.01494 -0.0463 0.2784 1.0000 10.000 1.3271 0.02199 0.01547 -0.0448 0.2755 1.0000 10.250 1.3407 0.02256 0.01605 -0.0431 0.2722 1.0000 10.500 1.3537 0.02319 0.01667 -0.0415 0.2688 1.0000 10.750 1.3693 0.02370 0.01723 -0.0403 0.2638 1.0000 11.000 1.3830 0.02432 0.01788 -0.0388 0.2595 1.0000 11.250 1.3933 0.02515 0.01869 -0.0371 0.2545 1.0000 11.500 1.4076 0.02579 0.01936 -0.0358 0.2497 1.0000 11.750 1.4215 0.02646 0.02008 -0.0346 0.2459 1.0000 12.000 1.4319 0.02737 0.02100 -0.0330 0.2410 1.0000 12.250 1.4433 0.02825 0.02190 -0.0316 0.2355 1.0000 12.500 1.4540 0.02920 0.02287 -0.0302 0.2291 1.0000 12.750 1.4615 0.03038 0.02405 -0.0286 0.2222 1.0000 13.000 1.4711 0.03147 0.02516 -0.0273 0.2147 1.0000 13.250 1.4735 0.03311 0.02677 -0.0255 0.2024 1.0000 13.500 1.4762 0.03480 0.02843 -0.0238 0.1923 1.0000 13.750 1.4748 0.03687 0.03046 -0.0220 0.1788 1.0000 14.000 1.4747 0.03890 0.03248 -0.0204 0.1690 1.0000 14.250 1.4645 0.04186 0.03538 -0.0184 0.1521 1.0000 14.500 1.4584 0.04459 0.03810 -0.0168 0.1421 1.0000 14.750 1.4473 0.04789 0.04138 -0.0153 0.1301 1.0000 15.000 1.4404 0.05089 0.04441 -0.0141 0.1220 1.0000 15.250 1.4321 0.05416 0.04771 -0.0131 0.1161 1.0000 15.500 1.4255 0.05736 0.05095 -0.0124 0.1098 1.0000 15.750 1.4114 0.06147 0.05509 -0.0116 0.1033 1.0000 16.000 1.4033 0.06504 0.05873 -0.0113 0.0970 1.0000 16.250 1.3854 0.06989 0.06361 -0.0110 0.0883 1.0000 16.500 1.3583 0.07602 0.06974 -0.0110 0.0725 1.0000 16.750 1.3326 0.08217 0.07591 -0.0113 0.0621 1.0000 17.000 1.3075 0.08841 0.08218 -0.0119 0.0527 1.0000 17.250 1.2809 0.09498 0.08881 -0.0127 0.0428 1.0000