XFOIL Version 6.96 Calculated polar for: GOE 526 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3542 0.09489 0.09100 -0.0463 1.0000 0.0390 -10.000 -0.3628 0.09160 0.08776 -0.0463 0.9998 0.0395 -9.500 -0.5400 0.03461 0.02932 -0.0936 0.9491 0.0413 -9.250 -0.5289 0.03033 0.02435 -0.0947 0.9413 0.0421 -9.000 -0.5079 0.02910 0.02302 -0.0944 0.9324 0.0426 -8.750 -0.4816 0.02782 0.02161 -0.0951 0.9264 0.0432 -8.500 -0.4588 0.02658 0.02020 -0.0950 0.9187 0.0438 -8.250 -0.4351 0.02529 0.01869 -0.0949 0.9112 0.0445 -8.000 -0.4102 0.02400 0.01715 -0.0950 0.9045 0.0453 -7.750 -0.3875 0.02286 0.01576 -0.0944 0.8959 0.0462 -7.500 -0.3602 0.02173 0.01433 -0.0946 0.8903 0.0474 -7.250 -0.3377 0.02090 0.01336 -0.0938 0.8817 0.0483 -7.000 -0.3105 0.02023 0.01265 -0.0938 0.8754 0.0492 -6.750 -0.2852 0.01963 0.01197 -0.0934 0.8682 0.0502 -6.500 -0.2596 0.01899 0.01121 -0.0930 0.8611 0.0513 -6.000 -0.2081 0.01778 0.00971 -0.0921 0.8483 0.0539 -5.750 -0.1820 0.01723 0.00910 -0.0917 0.8420 0.0554 -5.500 -0.1555 0.01684 0.00868 -0.0914 0.8364 0.0571 -5.250 -0.1307 0.01647 0.00826 -0.0908 0.8297 0.0591 -5.000 -0.1040 0.01606 0.00773 -0.0904 0.8242 0.0613 -4.750 -0.0780 0.01564 0.00728 -0.0899 0.8188 0.0633 -4.500 -0.0532 0.01534 0.00697 -0.0892 0.8117 0.0656 -4.250 -0.0264 0.01504 0.00658 -0.0888 0.8053 0.0689 -4.000 -0.0015 0.01474 0.00626 -0.0881 0.7972 0.0722 -3.750 0.0244 0.01449 0.00598 -0.0875 0.7890 0.0760 -3.500 0.0501 0.01425 0.00567 -0.0868 0.7811 0.0804 -3.250 0.0753 0.01402 0.00545 -0.0861 0.7725 0.0853 -3.000 0.1018 0.01382 0.00520 -0.0856 0.7658 0.0913 -2.750 0.1267 0.01365 0.00508 -0.0849 0.7585 0.0982 -2.500 0.1531 0.01350 0.00491 -0.0844 0.7524 0.1061 -2.250 0.1793 0.01338 0.00477 -0.0839 0.7464 0.1150 -2.000 0.2046 0.01325 0.00470 -0.0833 0.7393 0.1242 -1.750 0.2312 0.01315 0.00455 -0.0828 0.7334 0.1338 -1.500 0.2568 0.01305 0.00448 -0.0822 0.7266 0.1440 -1.250 0.2822 0.01294 0.00439 -0.0815 0.7196 0.1536 -0.750 0.3333 0.01274 0.00422 -0.0803 0.7057 0.1749 -0.500 0.3591 0.01264 0.00412 -0.0797 0.6986 0.1868 -0.250 0.3842 0.01255 0.00408 -0.0789 0.6911 0.2011 0.000 0.4091 0.01244 0.00403 -0.0782 0.6832 0.2194 0.250 0.4336 0.01230 0.00398 -0.0774 0.6752 0.2462 0.500 0.4571 0.01211 0.00396 -0.0764 0.6660 0.2939 0.750 0.4776 0.01168 0.00396 -0.0750 0.6572 0.4202 1.250 0.5971 0.01078 0.00439 -0.0870 0.6343 0.9681 1.500 0.6492 0.01089 0.00438 -0.0919 0.6169 0.9866 1.750 0.7010 0.01096 0.00431 -0.0969 0.5963 0.9994 2.000 0.7239 0.01107 0.00432 -0.0958 0.5790 1.0000 2.250 0.7443 0.01120 0.00435 -0.0941 0.5622 1.0000 2.500 0.7643 0.01135 0.00440 -0.0925 0.5455 1.0000 2.750 0.7838 0.01152 0.00447 -0.0907 0.5280 1.0000 3.250 0.8206 0.01197 0.00467 -0.0868 0.4910 1.0000 3.500 0.8392 0.01221 0.00481 -0.0849 0.4761 1.0000 3.750 0.8580 0.01245 0.00498 -0.0831 0.4628 1.0000 4.000 0.8768 0.01270 0.00515 -0.0812 0.4513 1.0000 4.500 0.9143 0.01321 0.00555 -0.0776 0.4303 1.0000 4.750 0.9329 0.01349 0.00576 -0.0758 0.4210 1.0000 5.000 0.9522 0.01373 0.00599 -0.0741 0.4125 1.0000 5.250 0.9708 0.01402 0.00623 -0.0723 0.4044 1.0000 5.500 0.9898 0.01426 0.00647 -0.0705 0.3954 1.0000 5.750 1.0079 0.01456 0.00673 -0.0687 0.3873 1.0000 6.000 1.0264 0.01481 0.00699 -0.0669 0.3777 1.0000 6.250 1.0434 0.01511 0.00726 -0.0648 0.3679 1.0000 6.500 1.0602 0.01539 0.00753 -0.0627 0.3572 1.0000 6.750 1.0770 0.01568 0.00782 -0.0607 0.3470 1.0000 7.000 1.0917 0.01602 0.00812 -0.0583 0.3363 1.0000 7.250 1.1069 0.01632 0.00843 -0.0559 0.3233 1.0000 7.500 1.1202 0.01665 0.00876 -0.0533 0.3106 1.0000 7.750 1.1317 0.01701 0.00909 -0.0503 0.2977 1.0000 8.000 1.1426 0.01741 0.00947 -0.0474 0.2831 1.0000 8.250 1.1536 0.01787 0.00988 -0.0445 0.2668 1.0000 8.500 1.1632 0.01841 0.01037 -0.0416 0.2471 1.0000 8.750 1.1709 0.01909 0.01095 -0.0386 0.2261 1.0000 9.000 1.1788 0.01984 0.01161 -0.0357 0.2077 1.0000 9.250 1.1864 0.02066 0.01235 -0.0330 0.1928 1.0000 9.750 1.2043 0.02235 0.01398 -0.0282 0.1733 1.0000 10.000 1.2117 0.02334 0.01493 -0.0258 0.1656 1.0000 10.250 1.2232 0.02415 0.01579 -0.0240 0.1585 1.0000 10.500 1.2311 0.02520 0.01683 -0.0219 0.1520 1.0000 10.750 1.2424 0.02609 0.01778 -0.0203 0.1457 1.0000 11.000 1.2518 0.02713 0.01885 -0.0185 0.1388 1.0000 11.250 1.2611 0.02820 0.01996 -0.0169 0.1326 1.0000 11.500 1.2711 0.02927 0.02108 -0.0155 0.1251 1.0000 11.750 1.2797 0.03047 0.02230 -0.0140 0.1185 1.0000 12.000 1.2877 0.03175 0.02362 -0.0126 0.1111 1.0000 12.250 1.2951 0.03311 0.02501 -0.0112 0.1050 1.0000 12.500 1.3011 0.03463 0.02654 -0.0099 0.0992 1.0000 12.750 1.3066 0.03622 0.02817 -0.0087 0.0946 1.0000 13.000 1.3113 0.03793 0.02990 -0.0075 0.0901 1.0000 13.250 1.3135 0.03991 0.03190 -0.0064 0.0867 1.0000 13.500 1.3185 0.04170 0.03377 -0.0054 0.0836 1.0000 13.750 1.3219 0.04368 0.03582 -0.0046 0.0807 1.0000 14.000 1.3233 0.04591 0.03810 -0.0038 0.0783 1.0000 14.250 1.3230 0.04838 0.04060 -0.0031 0.0761 1.0000 14.500 1.3274 0.05045 0.04278 -0.0026 0.0738 1.0000 14.750 1.3300 0.05276 0.04519 -0.0022 0.0716 1.0000 15.000 1.3307 0.05533 0.04783 -0.0019 0.0697 1.0000 15.250 1.3295 0.05818 0.05073 -0.0017 0.0679 1.0000 15.500 1.3296 0.06095 0.05356 -0.0017 0.0663 1.0000 15.750 1.3321 0.06352 0.05626 -0.0017 0.0645 1.0000 16.000 1.3332 0.06630 0.05914 -0.0018 0.0628 1.0000 16.250 1.3331 0.06930 0.06223 -0.0022 0.0611 1.0000 16.500 1.3315 0.07255 0.06553 -0.0026 0.0597 1.0000 16.750 1.3294 0.07585 0.06887 -0.0031 0.0583 1.0000 17.000 1.3303 0.07890 0.07207 -0.0037 0.0568 1.0000 17.250 1.3301 0.08213 0.07542 -0.0044 0.0553 1.0000 17.500 1.3288 0.08558 0.07896 -0.0052 0.0538 1.0000 17.750 1.3271 0.08909 0.08255 -0.0062 0.0526 1.0000 18.000 1.3244 0.09274 0.08625 -0.0072 0.0516 1.0000 18.250 1.3223 0.09637 0.08997 -0.0083 0.0503 1.0000 18.500 1.3209 0.09999 0.09373 -0.0095 0.0492 1.0000 18.750 1.3184 0.10380 0.09765 -0.0108 0.0479 1.0000 19.000 1.3153 0.10776 0.10172 -0.0124 0.0467 1.0000 19.250 1.3122 0.11169 0.10572 -0.0139 0.0458 1.0000