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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.5730 0.10181 0.09788 -0.0462 1.0000 0.0637 -14.750 -0.6263 0.08782 0.08375 -0.0548 1.0000 0.0625 -14.500 -0.7351 0.06930 0.06475 -0.0674 1.0000 0.0606 -14.250 -0.7946 0.06022 0.05526 -0.0720 1.0000 0.0600 -14.000 -0.8234 0.05520 0.04998 -0.0732 1.0000 0.0599 -13.750 -0.8394 0.05172 0.04631 -0.0732 1.0000 0.0602 -13.500 -0.8505 0.04892 0.04335 -0.0724 1.0000 0.0606 -13.250 -0.8603 0.04647 0.04072 -0.0709 1.0000 0.0611 -13.000 -0.8698 0.04433 0.03842 -0.0685 1.0000 0.0617 -12.750 -0.8801 0.04253 0.03646 -0.0652 1.0000 0.0622 -12.500 -0.8642 0.03961 0.03310 -0.0671 0.9407 0.0633 -12.250 -0.8543 0.03755 0.03055 -0.0660 0.8814 0.0640 -12.000 -0.8340 0.03608 0.02897 -0.0650 0.8418 0.0649 -11.750 -0.8167 0.03515 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0.00986 -0.0327 0.4852 0.8140 2.750 0.6008 0.01725 0.00988 -0.0323 0.4811 0.8327 3.000 0.6287 0.01725 0.00986 -0.0320 0.4776 0.8533 3.250 0.6539 0.01744 0.01014 -0.0314 0.4732 0.8756 3.500 0.6808 0.01760 0.01042 -0.0311 0.4678 0.8991 3.750 0.7154 0.01769 0.01051 -0.0323 0.4632 0.9208 4.000 0.7566 0.01779 0.01051 -0.0348 0.4593 0.9395 4.250 0.7974 0.01814 0.01089 -0.0376 0.4544 0.9562 4.500 0.8408 0.01844 0.01124 -0.0411 0.4491 0.9698 4.750 0.8878 0.01862 0.01136 -0.0452 0.4448 0.9804 5.000 0.9377 0.01877 0.01139 -0.0498 0.4412 0.9882 5.250 0.9840 0.01916 0.01184 -0.0542 0.4366 0.9966 5.500 1.0098 0.01945 0.01218 -0.0547 0.4323 1.0000 5.750 1.0244 0.01962 0.01233 -0.0528 0.4289 1.0000 6.000 1.0436 0.01976 0.01240 -0.0515 0.4258 1.0000 6.250 1.0666 0.01996 0.01249 -0.0509 0.4231 1.0000 6.500 1.0810 0.02042 0.01302 -0.0489 0.4198 1.0000 6.750 1.0954 0.02087 0.01355 -0.0470 0.4162 1.0000 7.000 1.1137 0.02124 0.01394 -0.0457 0.4130 1.0000 7.250 1.1353 0.02153 0.01421 -0.0449 0.4102 1.0000 7.500 1.1601 0.02179 0.01442 -0.0445 0.4078 1.0000 7.750 1.1878 0.02214 0.01469 -0.0448 0.4054 1.0000 8.000 1.1999 0.02279 0.01548 -0.0426 0.4022 1.0000 8.250 1.2143 0.02338 0.01617 -0.0409 0.3988 1.0000 8.500 1.2332 0.02388 0.01673 -0.0399 0.3959 1.0000 8.750 1.2566 0.02419 0.01704 -0.0395 0.3931 1.0000 9.000 1.2863 0.02429 0.01705 -0.0400 0.3901 1.0000 9.250 1.3086 0.02472 0.01748 -0.0395 0.3866 1.0000 9.500 1.3155 0.02541 0.01833 -0.0369 0.3824 1.0000 9.750 1.3321 0.02586 0.01885 -0.0356 0.3788 1.0000 10.000 1.3558 0.02615 0.01914 -0.0353 0.3759 1.0000 10.250 1.3859 0.02635 0.01927 -0.0360 0.3732 1.0000 10.500 1.4116 0.02688 0.01979 -0.0361 0.3705 1.0000 10.750 1.4102 0.02794 0.02107 -0.0327 0.3672 1.0000 11.000 1.4144 0.02883 0.02208 -0.0300 0.3639 1.0000 11.250 1.4279 0.02941 0.02271 -0.0285 0.3609 1.0000 11.500 1.4572 0.02950 0.02276 -0.0290 0.3578 1.0000 11.750 1.5013 0.02947 0.02261 -0.0316 0.3542 1.0000 12.000 1.4768 0.03108 0.02446 -0.0255 0.3510 1.0000 12.250 1.4652 0.03268 0.02623 -0.0220 0.3471 1.0000 12.500 1.4821 0.03306 0.02661 -0.0212 0.3431 1.0000 12.750 1.5350 0.03196 0.02534 -0.0236 0.3389 1.0000 13.000 1.5153 0.03415 0.02772 -0.0199 0.3352 1.0000 13.250 1.4890 0.03713 0.03091 -0.0168 0.3308 1.0000 13.500 1.5039 0.03773 0.03153 -0.0163 0.3266 1.0000 13.750 1.5581 0.03600 0.02963 -0.0178 0.3224 1.0000 14.000 1.5193 0.04019 0.03408 -0.0148 0.3181 1.0000 14.250 1.4877 0.04454 0.03861 -0.0133 0.3128 1.0000 14.500 1.5236 0.04347 0.03747 -0.0135 0.3086 1.0000 14.750 1.5467 0.04359 0.03756 -0.0133 0.3043 1.0000 15.000 1.4636 0.05309 0.04740 -0.0120 0.2974 1.0000 15.250 1.4994 0.05174 0.04599 -0.0119 0.2930 1.0000 15.500 1.5253 0.05142 0.04563 -0.0118 0.2884 1.0000 15.750 1.4365 0.06289 0.05741 -0.0120 0.2799 1.0000 16.000 1.4926 0.05912 0.05351 -0.0117 0.2759 1.0000 16.250 1.3927 0.07311 0.06780 -0.0131 0.2657 1.0000 16.500 1.4447 0.06949 0.06409 -0.0128 0.2618 1.0000 16.750 1.3708 0.08135 0.07615 -0.0146 0.2515 1.0000 17.000 1.4104 0.07914 0.07389 -0.0144 0.2473 1.0000 17.250 1.3597 0.08858 0.08346 -0.0161 0.2380 1.0000 17.500 1.3836 0.08837 0.08323 -0.0162 0.2332 1.0000 17.750 1.3887 0.09062 0.08550 -0.0167 0.2274 1.0000 18.000 1.3662 0.09667 0.09163 -0.0182 0.2197 1.0000 18.250 1.4005 0.09495 0.08983 -0.0178 0.2154 1.0000 18.500 1.3573 0.10397 0.09900 -0.0201 0.2068 1.0000 18.750 1.3979 0.10126 0.09617 -0.0195 0.2024 1.0000