XFOIL Version 6.96 Calculated polar for: GOE 770 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1454 0.08038 0.07652 -0.0479 1.0000 0.0274 -19.500 -1.1502 0.07623 0.07229 -0.0499 1.0000 0.0276 -19.250 -1.1542 0.07226 0.06825 -0.0518 1.0000 0.0278 -19.000 -1.1574 0.06845 0.06437 -0.0535 1.0000 0.0280 -18.750 -1.1597 0.06482 0.06067 -0.0550 1.0000 0.0282 -18.500 -1.1611 0.06142 0.05720 -0.0564 1.0000 0.0284 -18.250 -1.1613 0.05824 0.05395 -0.0576 1.0000 0.0286 -18.000 -1.1608 0.05521 0.05084 -0.0587 1.0000 0.0288 -17.750 -1.1596 0.05231 0.04787 -0.0597 1.0000 0.0291 -17.500 -1.1571 0.04963 0.04511 -0.0605 1.0000 0.0293 -17.250 -1.1530 0.04719 0.04259 -0.0612 1.0000 0.0294 -17.000 -1.1469 0.04497 0.04030 -0.0618 1.0000 0.0296 -16.750 -1.1503 0.04198 0.03725 -0.0623 1.0000 0.0300 -16.500 -1.1501 0.03931 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0.6114 2.500 0.6214 0.00856 0.00280 -0.0412 0.4140 0.6198 2.750 0.6498 0.00864 0.00286 -0.0414 0.4084 0.6278 3.000 0.6781 0.00871 0.00294 -0.0415 0.4032 0.6366 3.250 0.7067 0.00874 0.00301 -0.0417 0.3982 0.6470 3.500 0.7346 0.00883 0.00310 -0.0418 0.3925 0.6579 3.750 0.7622 0.00892 0.00321 -0.0419 0.3870 0.6712 4.000 0.7903 0.00895 0.00330 -0.0420 0.3824 0.6877 4.250 0.8175 0.00902 0.00342 -0.0420 0.3772 0.7078 4.500 0.8438 0.00914 0.00357 -0.0418 0.3713 0.7303 4.750 0.8713 0.00916 0.00368 -0.0419 0.3676 0.7557 5.250 0.9232 0.00928 0.00399 -0.0413 0.3588 0.8229 5.500 0.9476 0.00939 0.00419 -0.0407 0.3543 0.8586 5.750 0.9736 0.00943 0.00434 -0.0404 0.3518 0.8915 6.000 0.9991 0.00951 0.00451 -0.0399 0.3487 0.9227 6.250 1.0276 0.00966 0.00471 -0.0402 0.3454 0.9508 6.500 1.0607 0.00990 0.00493 -0.0415 0.3417 0.9693 6.750 1.0944 0.01017 0.00518 -0.0431 0.3376 0.9816 7.000 1.1310 0.01032 0.00535 -0.0452 0.3351 0.9896 7.250 1.1686 0.01050 0.00554 -0.0475 0.3317 0.9941 7.500 1.2062 0.01074 0.00576 -0.0500 0.3282 0.9977 7.750 1.2376 0.01101 0.00601 -0.0512 0.3246 1.0000 8.000 1.2544 0.01126 0.00623 -0.0494 0.3214 1.0000 8.250 1.2756 0.01137 0.00638 -0.0483 0.3196 1.0000 8.500 1.2965 0.01151 0.00654 -0.0472 0.3173 1.0000 8.750 1.3169 0.01169 0.00673 -0.0461 0.3144 1.0000 9.000 1.3364 0.01193 0.00696 -0.0449 0.3110 1.0000 9.250 1.3542 0.01226 0.00726 -0.0435 0.3071 1.0000 9.500 1.3748 0.01250 0.00752 -0.0425 0.3047 1.0000 9.750 1.3964 0.01267 0.00773 -0.0417 0.3027 1.0000 10.000 1.4166 0.01288 0.00797 -0.0407 0.3004 1.0000 10.250 1.4356 0.01315 0.00826 -0.0396 0.2979 1.0000 10.500 1.4537 0.01349 0.00861 -0.0384 0.2952 1.0000 10.750 1.4698 0.01394 0.00906 -0.0370 0.2919 1.0000 11.000 1.4877 0.01436 0.00950 -0.0360 0.2888 1.0000 11.250 1.5093 0.01465 0.00984 -0.0356 0.2865 1.0000 11.500 1.5292 0.01503 0.01025 -0.0350 0.2839 1.0000 11.750 1.5471 0.01553 0.01077 -0.0342 0.2809 1.0000 12.000 1.5620 0.01621 0.01146 -0.0333 0.2772 1.0000 12.250 1.5766 0.01696 0.01222 -0.0324 0.2736 1.0000 12.500 1.5966 0.01745 0.01277 -0.0321 0.2709 1.0000 12.750 1.6135 0.01815 0.01351 -0.0317 0.2668 1.0000 13.000 1.6254 0.01922 0.01458 -0.0310 0.2620 1.0000 13.250 1.6383 0.02028 0.01567 -0.0304 0.2575 1.0000 13.500 1.6531 0.02125 0.01668 -0.0301 0.2525 1.0000 13.750 1.6595 0.02291 0.01834 -0.0295 0.2460 1.0000 14.000 1.6697 0.02432 0.01979 -0.0291 0.2397 1.0000 14.250 1.6716 0.02646 0.02192 -0.0286 0.2315 1.0000 14.500 1.6753 0.02849 0.02397 -0.0281 0.2234 1.0000 14.750 1.6691 0.03142 0.02689 -0.0274 0.2139 1.0000 15.000 1.6572 0.03484 0.03030 -0.0265 0.2027 1.0000 15.250 1.6426 0.03850 0.03396 -0.0256 0.1917 1.0000 15.500 1.6267 0.04238 0.03784 -0.0248 0.1821 1.0000 15.750 1.6104 0.04640 0.04186 -0.0241 0.1741 1.0000 16.000 1.5965 0.05031 0.04578 -0.0237 0.1666 1.0000 16.250 1.5859 0.05394 0.04943 -0.0234 0.1607 1.0000 16.500 1.5739 0.05785 0.05336 -0.0232 0.1550 1.0000 16.750 1.5639 0.06160 0.05714 -0.0232 0.1500 1.0000 17.000 1.5574 0.06498 0.06056 -0.0232 0.1448 1.0000 17.250 1.5431 0.06934 0.06494 -0.0233 0.1400 1.0000 17.500 1.5388 0.07262 0.06826 -0.0235 0.1353 1.0000 17.750 1.5263 0.07684 0.07250 -0.0237 0.1301 1.0000 18.000 1.5172 0.08078 0.07648 -0.0241 0.1251 1.0000 18.250 1.5044 0.08519 0.08091 -0.0246 0.1193 1.0000 18.500 1.4938 0.08939 0.08513 -0.0251 0.1134 1.0000 18.750 1.4768 0.09443 0.09019 -0.0259 0.1072 1.0000 19.000 1.4621 0.09928 0.09504 -0.0267 0.0999 1.0000 19.250 1.4460 0.10436 0.10012 -0.0277 0.0918 1.0000