XFOIL Version 6.96 Calculated polar for: GOE 238 (HANSA-BRANDENBURG) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.2427 0.09873 0.09547 -0.0416 0.6103 0.0136 -9.750 -0.2369 0.09575 0.09250 -0.0428 0.6058 0.0140 -9.500 -0.2411 0.09067 0.08741 -0.0450 0.6021 0.0150 -9.250 -0.2347 0.08815 0.08488 -0.0460 0.5971 0.0151 -9.000 -0.2268 0.08600 0.08271 -0.0468 0.5926 0.0152 -8.750 -0.2192 0.08381 0.08053 -0.0477 0.5878 0.0153 -8.500 -0.2120 0.08166 0.07837 -0.0485 0.5828 0.0155 -8.000 -0.2034 0.07684 0.07355 -0.0500 0.5734 0.0158 -7.750 -0.2039 0.07434 0.07106 -0.0505 0.5692 0.0160 -7.500 -0.2033 0.07190 0.06863 -0.0515 0.5643 0.0162 -7.250 -0.1974 0.06892 0.06562 -0.0537 0.5600 0.0163 -7.000 -0.1900 0.06558 0.06228 -0.0564 0.5558 0.0167 -6.750 -0.1894 0.05821 0.05483 -0.0626 0.5531 0.0179 -6.500 -0.1737 0.05588 0.05246 -0.0642 0.5483 0.0180 -6.250 -0.1569 0.05346 0.04998 -0.0658 0.5439 0.0181 -6.000 -0.1388 0.05100 0.04747 -0.0674 0.5400 0.0182 -5.750 -0.1194 0.04880 0.04522 -0.0687 0.5354 0.0185 -5.500 -0.0997 0.04609 0.04242 -0.0703 0.5310 0.0186 -5.250 -0.0790 0.04335 0.03958 -0.0717 0.5271 0.0189 -5.000 -0.0573 0.04044 0.03658 -0.0730 0.5233 0.0193 -4.750 -0.0350 0.03712 0.03311 -0.0742 0.5193 0.0199 -4.500 -0.0131 0.03236 0.02812 -0.0753 0.5154 0.0204 -4.250 0.0024 0.02236 0.01745 -0.0754 0.5130 0.0213 -4.000 0.0259 0.02044 0.01533 -0.0751 0.5091 0.0215 -3.750 0.0506 0.01909 0.01380 -0.0747 0.5046 0.0218 -3.500 0.0748 0.01740 0.01188 -0.0742 0.5002 0.0221 -3.250 0.0997 0.01604 0.01030 -0.0737 0.4959 0.0225 -3.000 0.1223 0.01304 0.00682 -0.0727 0.4929 0.0232 -2.750 0.1483 0.01202 0.00560 -0.0723 0.4892 0.0236 -2.500 0.1750 0.01139 0.00484 -0.0720 0.4852 0.0239 -2.250 0.2019 0.01096 0.00430 -0.0717 0.4813 0.0242 -2.000 0.2291 0.01069 0.00396 -0.0714 0.4773 0.0246 -1.750 0.2565 0.01045 0.00365 -0.0711 0.4720 0.0248 -1.500 0.2832 0.01007 0.00319 -0.0708 0.4663 0.0251 -1.250 0.3100 0.00979 0.00287 -0.0705 0.4620 0.0255 -1.000 0.3375 0.00962 0.00268 -0.0703 0.4590 0.0258 -0.750 0.3649 0.00948 0.00253 -0.0700 0.4556 0.0262 -0.500 0.3922 0.00936 0.00240 -0.0698 0.4518 0.0265 -0.250 0.4194 0.00925 0.00226 -0.0695 0.4481 0.0269 0.000 0.4468 0.00915 0.00215 -0.0693 0.4447 0.0273 0.250 0.4742 0.00904 0.00203 -0.0691 0.4413 0.0278 0.500 0.5015 0.00896 0.00193 -0.0688 0.4372 0.0283 0.750 0.5287 0.00890 0.00185 -0.0686 0.4334 0.0287 1.000 0.5560 0.00887 0.00181 -0.0684 0.4301 0.0291 1.250 0.5834 0.00877 0.00173 -0.0681 0.4280 0.0302 1.500 0.6109 0.00873 0.00171 -0.0680 0.4255 0.0311 1.750 0.6384 0.00870 0.00169 -0.0678 0.4228 0.0320 2.000 0.6658 0.00869 0.00168 -0.0676 0.4200 0.0330 2.250 0.6931 0.00869 0.00168 -0.0674 0.4171 0.0339 2.500 0.7203 0.00870 0.00169 -0.0672 0.4139 0.0356 2.750 0.7479 0.00869 0.00172 -0.0671 0.4106 0.0379 3.000 0.7751 0.00872 0.00175 -0.0669 0.4041 0.0411 3.250 0.8021 0.00878 0.00181 -0.0667 0.3987 0.0460 3.500 0.8294 0.00879 0.00186 -0.0665 0.3941 0.0518 3.750 0.8565 0.00885 0.00192 -0.0663 0.3875 0.0577 4.000 0.8834 0.00892 0.00199 -0.0661 0.3823 0.0656 4.250 0.9104 0.00891 0.00207 -0.0660 0.3773 0.0971 4.500 0.9366 0.00889 0.00220 -0.0657 0.3700 0.1995 4.750 0.9905 0.00761 0.00252 -0.0722 0.3512 1.0000 5.000 1.0150 0.00784 0.00266 -0.0716 0.3323 1.0000 5.250 1.0330 0.00863 0.00310 -0.0701 0.2657 1.0000 5.500 1.0542 0.00916 0.00346 -0.0690 0.2364 1.0000 5.750 1.0776 0.00947 0.00371 -0.0683 0.2234 1.0000 6.000 1.1013 0.00976 0.00395 -0.0676 0.2137 1.0000 6.250 1.1255 0.01001 0.00417 -0.0670 0.2063 1.0000 6.500 1.1493 0.01029 0.00442 -0.0664 0.1985 1.0000 6.750 1.1735 0.01053 0.00463 -0.0658 0.1913 1.0000 7.000 1.1969 0.01083 0.00490 -0.0651 0.1827 1.0000 7.250 1.2194 0.01119 0.00519 -0.0643 0.1688 1.0000 7.750 1.2453 0.01335 0.00677 -0.0602 0.0678 1.0000 8.000 1.2661 0.01378 0.00718 -0.0592 0.0620 1.0000 8.250 1.2868 0.01419 0.00759 -0.0582 0.0570 1.0000 8.500 1.3082 0.01454 0.00795 -0.0573 0.0550 1.0000 8.750 1.3282 0.01497 0.00837 -0.0562 0.0520 1.0000 9.000 1.3474 0.01542 0.00882 -0.0551 0.0493 1.0000 9.250 1.3663 0.01586 0.00928 -0.0539 0.0471 1.0000 9.500 1.3860 0.01623 0.00968 -0.0528 0.0462 1.0000 9.750 1.4043 0.01664 0.01012 -0.0515 0.0447 1.0000 10.000 1.4211 0.01711 0.01061 -0.0501 0.0432 1.0000 10.250 1.4340 0.01762 0.01115 -0.0479 0.0418 1.0000 10.500 1.4441 0.01821 0.01175 -0.0454 0.0404 1.0000 10.750 1.4542 0.01888 0.01245 -0.0432 0.0390 1.0000 11.000 1.4664 0.01953 0.01315 -0.0415 0.0381 1.0000 11.250 1.4773 0.02037 0.01403 -0.0400 0.0368 1.0000 11.500 1.4873 0.02143 0.01514 -0.0389 0.0356 1.0000 11.750 1.4967 0.02275 0.01650 -0.0382 0.0339 1.0000 12.000 1.5058 0.02423 0.01800 -0.0376 0.0322 1.0000 12.250 1.5165 0.02562 0.01945 -0.0373 0.0311 1.0000 12.500 1.5256 0.02721 0.02107 -0.0369 0.0292 1.0000 12.750 1.5321 0.02906 0.02295 -0.0365 0.0267 1.0000 13.000 1.5385 0.03093 0.02485 -0.0362 0.0242 1.0000 13.250 1.5424 0.03305 0.02700 -0.0358 0.0218 1.0000 13.500 1.5452 0.03529 0.02927 -0.0354 0.0196 1.0000 13.750 1.5465 0.03769 0.03170 -0.0350 0.0179 1.0000 14.000 1.5480 0.04007 0.03414 -0.0347 0.0167 1.0000 14.250 1.5479 0.04264 0.03676 -0.0343 0.0156 1.0000 14.500 1.5474 0.04525 0.03942 -0.0340 0.0148 1.0000 14.750 1.5475 0.04782 0.04205 -0.0338 0.0142 1.0000 15.000 1.5472 0.05052 0.04482 -0.0336 0.0137 1.0000 15.250 1.5452 0.05348 0.04784 -0.0335 0.0129 1.0000 15.500 1.5446 0.05635 0.05077 -0.0336 0.0125 1.0000 15.750 1.5429 0.05938 0.05386 -0.0336 0.0119 1.0000 16.000 1.5420 0.06236 0.05692 -0.0337 0.0115 1.0000 16.250 1.5415 0.06530 0.05992 -0.0339 0.0113 1.0000 16.500 1.5404 0.06838 0.06306 -0.0341 0.0109 1.0000 16.750 1.5382 0.07162 0.06637 -0.0344 0.0106 1.0000 17.000 1.5361 0.07483 0.06965 -0.0347 0.0103 1.0000 17.250 1.5321 0.07838 0.07327 -0.0351 0.0100 1.0000 17.500 1.5283 0.08193 0.07689 -0.0356 0.0097 1.0000 17.750 1.5240 0.08557 0.08060 -0.0362 0.0095 1.0000