XFOIL Version 6.96 Calculated polar for: GOE 629 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 ------ -------- --------- --------- -------- -------- -------- -17.000 -0.9368 0.08033 0.07672 -0.0667 1.0000 0.0311 -16.750 -0.9689 0.07254 0.06883 -0.0710 1.0000 0.0312 -16.500 -1.0072 0.06394 0.06010 -0.0758 1.0000 0.0312 -16.250 -1.0448 0.05535 0.05138 -0.0808 1.0000 0.0311 -16.000 -1.0802 0.04668 0.04254 -0.0865 1.0000 0.0309 -15.750 -1.1050 0.03949 0.03515 -0.0917 1.0000 0.0312 -15.500 -1.1220 0.03471 0.03020 -0.0944 1.0000 0.0316 -15.250 -1.1413 0.03121 0.02660 -0.0943 1.0000 0.0323 -15.000 -1.1542 0.02912 0.02442 -0.0920 1.0000 0.0330 -14.750 -1.1647 0.02770 0.02293 -0.0884 1.0000 0.0339 -14.500 -1.1760 0.02671 0.02187 -0.0835 1.0000 0.0350 -14.250 -1.1893 0.02604 0.02111 -0.0775 1.0000 0.0359 -14.000 -1.1992 0.02512 0.02015 -0.0722 1.0000 0.0372 -13.750 -1.2003 0.02434 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0.750 0.3750 0.00727 0.00226 -0.0662 0.6585 0.7153 1.000 0.3951 0.00710 0.00235 -0.0642 0.6459 0.8099 1.250 0.4259 0.00710 0.00249 -0.0643 0.6333 0.8833 1.500 0.4719 0.00726 0.00265 -0.0679 0.6197 0.9257 1.750 0.5145 0.00743 0.00279 -0.0708 0.6071 0.9463 2.000 0.5547 0.00762 0.00292 -0.0732 0.5955 0.9593 2.250 0.5918 0.00783 0.00305 -0.0750 0.5846 0.9701 2.500 0.6325 0.00800 0.00319 -0.0776 0.5724 0.9779 2.750 0.6717 0.00818 0.00330 -0.0799 0.5588 0.9842 3.000 0.7141 0.00837 0.00341 -0.0830 0.5437 0.9906 3.250 0.7579 0.00854 0.00351 -0.0863 0.5270 0.9963 3.500 0.7974 0.00869 0.00359 -0.0889 0.5119 1.0000 3.750 0.8161 0.00880 0.00366 -0.0870 0.4994 1.0000 4.000 0.8349 0.00891 0.00374 -0.0851 0.4857 1.0000 4.250 0.8532 0.00904 0.00382 -0.0832 0.4704 1.0000 4.500 0.8708 0.00920 0.00392 -0.0811 0.4529 1.0000 4.750 0.8878 0.00938 0.00403 -0.0788 0.4331 1.0000 5.000 0.9040 0.00960 0.00416 -0.0764 0.4122 1.0000 5.250 0.9205 0.00982 0.00431 -0.0741 0.3911 1.0000 5.500 0.9354 0.01012 0.00449 -0.0715 0.3686 1.0000 5.750 0.9508 0.01042 0.00470 -0.0690 0.3505 1.0000 6.000 0.9670 0.01070 0.00492 -0.0667 0.3352 1.0000 6.250 0.9833 0.01098 0.00514 -0.0644 0.3210 1.0000 6.500 0.9998 0.01126 0.00538 -0.0621 0.3080 1.0000 6.750 1.0157 0.01156 0.00562 -0.0598 0.2938 1.0000 7.000 1.0314 0.01188 0.00588 -0.0574 0.2776 1.0000 7.250 1.0467 0.01220 0.00614 -0.0549 0.2616 1.0000 7.500 1.0599 0.01252 0.00640 -0.0521 0.2441 1.0000 7.750 1.0714 0.01290 0.00669 -0.0490 0.2226 1.0000 8.000 1.0813 0.01338 0.00704 -0.0457 0.1981 1.0000 8.250 1.0911 0.01393 0.00746 -0.0425 0.1753 1.0000 8.750 1.1138 0.01504 0.00840 -0.0368 0.1436 1.0000 9.000 1.1266 0.01558 0.00888 -0.0344 0.1303 1.0000 9.250 1.1393 0.01615 0.00940 -0.0320 0.1173 1.0000 9.500 1.1520 0.01674 0.00993 -0.0296 0.1051 1.0000 9.750 1.1634 0.01742 0.01055 -0.0272 0.0922 1.0000 10.000 1.1741 0.01817 0.01124 -0.0248 0.0794 1.0000 10.250 1.1838 0.01900 0.01201 -0.0223 0.0655 1.0000 10.500 1.1922 0.01994 0.01286 -0.0198 0.0546 1.0000 10.750 1.2025 0.02080 0.01370 -0.0176 0.0493 1.0000 11.000 1.2119 0.02174 0.01464 -0.0154 0.0461 1.0000 11.250 1.2227 0.02263 0.01557 -0.0135 0.0440 1.0000 11.500 1.2321 0.02365 0.01661 -0.0116 0.0425 1.0000 11.750 1.2388 0.02487 0.01786 -0.0095 0.0411 1.0000 12.000 1.2464 0.02609 0.01914 -0.0077 0.0401 1.0000 12.250 1.2556 0.02724 0.02036 -0.0061 0.0391 1.0000 12.500 1.2633 0.02855 0.02173 -0.0046 0.0383 1.0000 12.750 1.2702 0.02997 0.02321 -0.0031 0.0374 1.0000 13.000 1.2755 0.03156 0.02485 -0.0017 0.0367 1.0000 13.250 1.2780 0.03344 0.02678 -0.0003 0.0360 1.0000 13.500 1.2774 0.03567 0.02906 0.0010 0.0354 1.0000 13.750 1.2794 0.03775 0.03121 0.0021 0.0348 1.0000 14.000 1.2849 0.03960 0.03316 0.0029 0.0344 1.0000 14.250 1.2900 0.04155 0.03519 0.0035 0.0338 1.0000 14.500 1.2938 0.04367 0.03739 0.0041 0.0333 1.0000 14.750 1.2966 0.04594 0.03973 0.0046 0.0328 1.0000 15.000 1.2990 0.04832 0.04218 0.0050 0.0323 1.0000 15.250 1.3011 0.05078 0.04470 0.0052 0.0318 1.0000 15.500 1.3020 0.05339 0.04737 0.0054 0.0315 1.0000 15.750 1.3014 0.05617 0.05019 0.0056 0.0309 1.0000 16.000 1.3001 0.05897 0.05303 0.0059 0.0305 1.0000 16.250 1.3009 0.06163 0.05575 0.0061 0.0300 1.0000 16.500 1.3036 0.06421 0.05843 0.0060 0.0298 1.0000 16.750 1.3053 0.06709 0.06141 0.0055 0.0292 1.0000 17.000 1.3070 0.06985 0.06426 0.0052 0.0289 1.0000 17.250 1.3076 0.07283 0.06733 0.0048 0.0285 1.0000 17.500 1.3084 0.07575 0.07033 0.0044 0.0281 1.0000 17.750 1.3086 0.07879 0.07345 0.0039 0.0278 1.0000 18.000 1.3085 0.08196 0.07667 0.0031 0.0273 1.0000 18.250 1.3092 0.08494 0.07970 0.0026 0.0269 1.0000 18.500 1.3105 0.08777 0.08257 0.0022 0.0266 1.0000 18.750 1.3143 0.08984 0.08463 0.0026 0.0261 1.0000 19.000 1.3130 0.09302 0.08791 0.0021 0.0257 1.0000 19.250 1.3075 0.09738 0.09241 0.0003 0.0254 1.0000