XFOIL Version 6.96 Calculated polar for: GOE 625 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.8189 0.05869 0.05522 -0.1082 0.9979 0.0487 -16.000 -0.8317 0.05027 0.04663 -0.1181 0.9944 0.0493 -15.750 -0.8301 0.04396 0.04016 -0.1269 0.9911 0.0499 -15.500 -0.8239 0.03905 0.03508 -0.1342 0.9855 0.0507 -15.250 -0.8145 0.03509 0.03091 -0.1403 0.9803 0.0515 -15.000 -0.8097 0.03212 0.02771 -0.1434 0.9704 0.0523 -14.750 -0.8025 0.03006 0.02549 -0.1444 0.9612 0.0530 -14.500 -0.7904 0.02904 0.02444 -0.1438 0.9521 0.0537 -14.250 -0.7782 0.02834 0.02372 -0.1426 0.9426 0.0543 -14.000 -0.7670 0.02771 0.02302 -0.1409 0.9338 0.0550 -13.750 -0.7581 0.02715 0.02238 -0.1387 0.9239 0.0557 -13.500 -0.7454 0.02646 0.02154 -0.1371 0.9163 0.0568 -13.250 -0.7328 0.02571 0.02060 -0.1356 0.9079 0.0578 -13.000 -0.7178 0.02490 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0.01306 0.00537 -0.1121 0.4404 0.3588 1.750 0.7810 0.01265 0.00552 -0.1117 0.4383 0.5314 2.000 0.8011 0.01212 0.00574 -0.1103 0.4355 0.7591 2.250 0.8175 0.01195 0.00598 -0.1073 0.4326 0.9119 2.500 0.8591 0.01215 0.00617 -0.1101 0.4291 0.9807 2.750 0.9049 0.01244 0.00636 -0.1141 0.4253 1.0000 3.000 0.9275 0.01268 0.00651 -0.1132 0.4217 1.0000 3.250 0.9482 0.01277 0.00661 -0.1119 0.4199 1.0000 3.500 0.9703 0.01290 0.00672 -0.1109 0.4179 1.0000 3.750 0.9931 0.01305 0.00685 -0.1101 0.4158 1.0000 4.000 1.0153 0.01321 0.00699 -0.1091 0.4135 1.0000 4.250 1.0370 0.01337 0.00713 -0.1081 0.4111 1.0000 4.500 1.0590 0.01357 0.00729 -0.1072 0.4087 1.0000 4.750 1.0830 0.01382 0.00748 -0.1067 0.4061 1.0000 5.000 1.1109 0.01413 0.00772 -0.1070 0.4033 1.0000 5.250 1.1315 0.01429 0.00791 -0.1058 0.4018 1.0000 5.500 1.1530 0.01447 0.00811 -0.1048 0.3999 1.0000 5.750 1.1750 0.01467 0.00833 -0.1040 0.3977 1.0000 6.000 1.1972 0.01488 0.00854 -0.1032 0.3954 1.0000 6.250 1.2191 0.01511 0.00876 -0.1024 0.3930 1.0000 6.500 1.2409 0.01536 0.00900 -0.1016 0.3904 1.0000 6.750 1.2642 0.01567 0.00925 -0.1012 0.3876 1.0000 7.000 1.2890 0.01598 0.00954 -0.1010 0.3847 1.0000 7.250 1.3084 0.01623 0.00985 -0.0999 0.3827 1.0000 7.500 1.3285 0.01650 0.01016 -0.0989 0.3802 1.0000 7.750 1.3482 0.01680 0.01047 -0.0979 0.3772 1.0000 8.000 1.3677 0.01711 0.01080 -0.0969 0.3742 1.0000 8.250 1.3874 0.01747 0.01113 -0.0960 0.3711 1.0000 8.500 1.4096 0.01787 0.01148 -0.0955 0.3674 1.0000 8.750 1.4273 0.01824 0.01194 -0.0944 0.3650 1.0000 9.000 1.4455 0.01865 0.01239 -0.0934 0.3618 1.0000 9.250 1.4633 0.01908 0.01285 -0.0924 0.3581 1.0000 9.500 1.4801 0.01958 0.01335 -0.0913 0.3541 1.0000 9.750 1.4969 0.02015 0.01389 -0.0902 0.3498 1.0000 10.000 1.5142 0.02067 0.01449 -0.0893 0.3458 1.0000 10.250 1.5312 0.02124 0.01510 -0.0884 0.3413 1.0000 10.500 1.5462 0.02192 0.01578 -0.0873 0.3367 1.0000 10.750 1.5610 0.02266 0.01652 -0.0862 0.3323 1.0000 11.000 1.5780 0.02330 0.01723 -0.0854 0.3272 1.0000 11.250 1.5916 0.02414 0.01808 -0.0843 0.3215 1.0000 11.500 1.6035 0.02510 0.01904 -0.0831 0.3161 1.0000 11.750 1.6180 0.02595 0.01994 -0.0822 0.3098 1.0000 12.000 1.6274 0.02713 0.02111 -0.0808 0.3033 1.0000 12.250 1.6391 0.02822 0.02222 -0.0797 0.2969 1.0000 12.500 1.6475 0.02958 0.02357 -0.0784 0.2897 1.0000 12.750 1.6549 0.03102 0.02501 -0.0771 0.2829 1.0000 13.000 1.6620 0.03254 0.02654 -0.0759 0.2758 1.0000 13.250 1.6651 0.03440 0.02838 -0.0744 0.2694 1.0000 13.500 1.6738 0.03588 0.02990 -0.0735 0.2636 1.0000 13.750 1.6773 0.03782 0.03183 -0.0722 0.2583 1.0000 14.000 1.6815 0.03971 0.03373 -0.0711 0.2537 1.0000 14.250 1.6892 0.04137 0.03545 -0.0703 0.2496 1.0000 14.500 1.6930 0.04340 0.03750 -0.0693 0.2453 1.0000 14.750 1.6943 0.04567 0.03977 -0.0682 0.2414 1.0000 15.000 1.6992 0.04768 0.04183 -0.0675 0.2382 1.0000 15.250 1.7059 0.04954 0.04377 -0.0669 0.2351 1.0000 15.500 1.7089 0.05178 0.04606 -0.0662 0.2318 1.0000 15.750 1.7096 0.05427 0.04857 -0.0654 0.2287 1.0000 16.000 1.7087 0.05691 0.05121 -0.0647 0.2254 1.0000 16.250 1.7131 0.05915 0.05355 -0.0643 0.2229 1.0000 16.500 1.7169 0.06145 0.05593 -0.0640 0.2201 1.0000 16.750 1.7172 0.06413 0.05868 -0.0636 0.2171 1.0000 17.000 1.7156 0.06703 0.06161 -0.0632 0.2143 1.0000 17.250 1.7134 0.06996 0.06454 -0.0628 0.2112 1.0000 17.500 1.7143 0.07270 0.06738 -0.0626 0.2088 1.0000 17.750 1.7148 0.07551 0.07029 -0.0626 0.2060 1.0000 18.000 1.7132 0.07854 0.07339 -0.0625 0.2031 1.0000 18.250 1.7097 0.08180 0.07669 -0.0625 0.2002 1.0000 18.500 1.7064 0.08500 0.07990 -0.0625 0.1973 1.0000 18.750 1.7049 0.08810 0.08309 -0.0626 0.1948 1.0000 19.000 1.7038 0.09118 0.08628 -0.0629 0.1919 1.0000 19.250 1.6989 0.09474 0.08991 -0.0632 0.1884 1.0000