XFOIL Version 6.96 Calculated polar for: GOE 570 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 -0.0704 0.05717 0.05209 -0.2303 0.7339 0.0523 -19.500 -0.0717 0.05480 0.04965 -0.2315 0.7292 0.0529 -19.250 -0.0677 0.05311 0.04789 -0.2320 0.7248 0.0529 -19.000 -0.0654 0.05131 0.04601 -0.2325 0.7203 0.0531 -18.750 -0.0610 0.04960 0.04426 -0.2331 0.7174 0.0532 -18.500 -0.0568 0.04797 0.04259 -0.2335 0.7143 0.0533 -18.250 -0.0549 0.04604 0.04060 -0.2343 0.7108 0.0539 -18.000 -0.0484 0.04481 0.03930 -0.2342 0.7070 0.0537 -17.750 -0.0446 0.04333 0.03775 -0.2343 0.7030 0.0539 -17.500 -0.0392 0.04185 0.03622 -0.2346 0.6997 0.0542 -17.250 -0.0355 0.04030 0.03463 -0.2348 0.6972 0.0544 -17.000 -0.0272 0.03924 0.03355 -0.2345 0.6943 0.0543 -16.750 -0.0228 0.03788 0.03213 -0.2344 0.6912 0.0545 -16.500 -0.0173 0.03670 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0.0833 -2.250 0.0712 0.01990 0.01240 -0.0382 0.4725 0.0918 -2.000 0.0903 0.02001 0.01257 -0.0373 0.4708 0.1008 -1.750 0.1081 0.02015 0.01279 -0.0364 0.4687 0.1147 -1.500 0.1276 0.02012 0.01302 -0.0359 0.4665 0.1651 -1.250 0.1450 0.02040 0.01336 -0.0349 0.4637 0.1810 -1.000 0.1613 0.02074 0.01371 -0.0338 0.4608 0.1891 -0.750 0.1736 0.02124 0.01420 -0.0321 0.4573 0.1946 -0.500 0.1896 0.02165 0.01456 -0.0309 0.4540 0.1983 -0.250 0.2089 0.02194 0.01489 -0.0304 0.4523 0.2032 0.000 0.2287 0.02223 0.01522 -0.0299 0.4504 0.2085 0.250 0.2469 0.02260 0.01559 -0.0292 0.4480 0.2115 0.500 0.2622 0.02310 0.01608 -0.0281 0.4453 0.2138 0.750 0.2779 0.02359 0.01654 -0.0271 0.4428 0.2156 1.000 0.2924 0.02411 0.01703 -0.0260 0.4395 0.2192 1.250 0.3110 0.02446 0.01737 -0.0254 0.4364 0.2244 1.500 0.3278 0.02496 0.01792 -0.0247 0.4348 0.2282 1.750 0.3458 0.02541 0.01840 -0.0242 0.4328 0.2320 2.000 0.3640 0.02588 0.01886 -0.0237 0.4305 0.2351 2.250 0.3825 0.02629 0.01932 -0.0234 0.4283 0.2452 2.500 0.3974 0.02690 0.01992 -0.0225 0.4258 0.2486 2.750 0.4112 0.02753 0.02061 -0.0216 0.4229 0.2683 3.000 0.4324 0.02764 0.02111 -0.0220 0.4196 0.3800 3.250 0.4507 0.02808 0.02175 -0.0218 0.4183 0.4244 3.500 0.4691 0.02854 0.02232 -0.0215 0.4167 0.4553 3.750 0.4861 0.02907 0.02294 -0.0210 0.4148 0.4757 4.000 0.5007 0.02974 0.02369 -0.0203 0.4126 0.4962 4.250 0.5151 0.03040 0.02441 -0.0196 0.4099 0.5183 4.500 0.5290 0.03103 0.02513 -0.0188 0.4073 0.5478 4.750 0.5437 0.03159 0.02576 -0.0180 0.4043 0.5759 5.000 0.5604 0.03193 0.02627 -0.0174 0.4023 0.6227 5.250 0.5669 0.03250 0.02721 -0.0152 0.4009 0.7084 5.500 0.7344 0.03528 0.03081 -0.0463 0.3988 0.9405 5.750 0.7266 0.03603 0.03157 -0.0411 0.3966 0.9533 6.000 0.7517 0.03710 0.03262 -0.0427 0.3944 0.9588 6.250 0.7741 0.03833 0.03382 -0.0440 0.3917 0.9647 6.500 0.7791 0.03934 0.03480 -0.0416 0.3893 0.9700 6.750 0.7989 0.04019 0.03559 -0.0419 0.3862 0.9731 7.000 0.8407 0.04172 0.03715 -0.0476 0.3850 0.9750 7.250 0.8855 0.04313 0.03856 -0.0537 0.3834 0.9776 7.500 0.9217 0.04440 0.03984 -0.0580 0.3815 0.9803 7.750 0.9490 0.04553 0.04096 -0.0604 0.3796 0.9826 8.000 0.9749 0.04676 0.04218 -0.0626 0.3776 0.9855 8.250 0.9867 0.04829 0.04370 -0.0625 0.3752 0.9876 8.500 1.0085 0.04970 0.04508 -0.0641 0.3727 0.9900 8.750 1.0441 0.05044 0.04577 -0.0680 0.3699 0.9916 9.000 1.0676 0.05173 0.04710 -0.0703 0.3686 0.9931 9.250 1.0953 0.05290 0.04829 -0.0731 0.3672 0.9953 9.500 1.1194 0.05429 0.04969 -0.0756 0.3653 0.9974 9.750 1.1452 0.05577 0.05119 -0.0785 0.3635 0.9994 10.000 1.1595 0.05699 0.05241 -0.0788 0.3615 0.9998 10.250 1.1698 0.05822 0.05362 -0.0784 0.3593 1.0000 10.500 1.1784 0.05935 0.05473 -0.0776 0.3569 1.0000 10.750 1.1938 0.05991 0.05524 -0.0773 0.3544 1.0000 11.000 1.1985 0.06144 0.05681 -0.0763 0.3532 1.0000 11.250 1.2058 0.06278 0.05820 -0.0756 0.3519 1.0000 11.500 1.2148 0.06399 0.05943 -0.0750 0.3504 1.0000 11.750 1.2229 0.06529 0.06075 -0.0743 0.3489 1.0000 12.000 1.2269 0.06693 0.06241 -0.0733 0.3469 1.0000 12.250 1.2348 0.06823 0.06371 -0.0727 0.3451 1.0000 12.500 1.2437 0.06944 0.06492 -0.0722 0.3433 1.0000 12.750 1.2544 0.07047 0.06592 -0.0718 0.3412 1.0000 13.000 1.2727 0.07081 0.06622 -0.0720 0.3388 1.0000 13.250 1.2719 0.07293 0.06840 -0.0709 0.3375 1.0000 13.500 1.2776 0.07447 0.06999 -0.0703 0.3364 1.0000 13.750 1.2829 0.07606 0.07161 -0.0697 0.3347 1.0000 14.000 1.2859 0.07787 0.07345 -0.0689 0.3328 1.0000 14.250 1.2891 0.07965 0.07526 -0.0682 0.3310 1.0000 14.500 1.2978 0.08093 0.07655 -0.0679 0.3295 1.0000 14.750 1.3066 0.08216 0.07777 -0.0676 0.3277 1.0000 15.000 1.3198 0.08298 0.07856 -0.0676 0.3257 1.0000 15.250 1.3381 0.08329 0.07885 -0.0680 0.3241 1.0000 15.500 1.3385 0.08533 0.08094 -0.0672 0.3226 1.0000 15.750 1.3368 0.08758 0.08325 -0.0663 0.3213 1.0000 16.000 1.3307 0.09029 0.08603 -0.0652 0.3183 1.0000 16.250 1.3317 0.09228 0.08806 -0.0646 0.3169 1.0000 16.500 1.3342 0.09417 0.08996 -0.0641 0.3146 1.0000 16.750 1.3417 0.09553 0.09129 -0.0639 0.3122 1.0000 17.000 1.3580 0.09599 0.09171 -0.0643 0.3097 1.0000 17.250 1.3739 0.09649 0.09220 -0.0646 0.3085 1.0000 17.500 1.3620 0.09975 0.09557 -0.0633 0.3072 1.0000 17.750 1.3545 0.10260 0.09849 -0.0624 0.3049 1.0000