XFOIL Version 6.96 Calculated polar for: GOE 683 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.6958 0.08071 0.07602 -0.0774 1.0000 0.0748 -15.500 -0.7723 0.06813 0.06313 -0.0848 1.0000 0.0742 -15.250 -0.8164 0.06133 0.05609 -0.0873 1.0000 0.0740 -15.000 -0.8536 0.05630 0.05081 -0.0874 1.0000 0.0740 -14.750 -0.8843 0.05263 0.04692 -0.0859 1.0000 0.0742 -14.500 -0.9102 0.04972 0.04378 -0.0831 1.0000 0.0744 -14.250 -0.9342 0.04738 0.04123 -0.0793 1.0000 0.0747 -14.000 -0.9550 0.04554 0.03918 -0.0747 1.0000 0.0749 -13.750 -0.9778 0.04411 0.03754 -0.0689 1.0000 0.0752 -13.500 -0.9756 0.04179 0.03515 -0.0666 1.0000 0.0759 -13.250 -0.9645 0.04027 0.03366 -0.0649 1.0000 0.0769 -13.000 -0.9636 0.03924 0.03261 -0.0615 1.0000 0.0777 -12.750 -0.9673 0.03843 0.03180 -0.0572 1.0000 0.0786 -12.500 -0.9945 0.03829 0.03164 -0.0490 1.0000 0.0787 -12.250 -0.9753 0.03696 0.03019 -0.0492 0.9948 0.0803 -12.000 -0.9507 0.03532 0.02830 -0.0504 0.9855 0.0818 -11.750 -0.9273 0.03389 0.02657 -0.0511 0.9760 0.0831 -11.500 -0.8855 0.03165 0.02432 -0.0548 0.9703 0.0850 -11.250 -0.8437 0.03027 0.02298 -0.0582 0.9650 0.0873 -11.000 -0.8122 0.02907 0.02167 -0.0597 0.9551 0.0895 -10.750 -0.7749 0.02778 0.02018 -0.0622 0.9487 0.0915 -10.500 -0.7316 0.02616 0.01858 -0.0658 0.9404 0.0941 -10.250 -0.6832 0.02498 0.01744 -0.0703 0.9340 0.0971 -10.000 -0.6387 0.02390 0.01624 -0.0741 0.9240 0.1004 -9.750 -0.5861 0.02258 0.01490 -0.0795 0.9151 0.1037 -9.500 -0.5410 0.02171 0.01403 -0.0834 0.9012 0.1075 -9.250 -0.5000 0.02099 0.01317 -0.0864 0.8869 0.1115 -9.000 -0.4636 0.02023 0.01242 -0.0885 0.8724 0.1154 -8.750 -0.4385 0.01983 0.01194 -0.0882 0.8567 0.1193 -8.500 -0.4187 0.01952 0.01150 -0.0867 0.8416 0.1237 -8.250 -0.3995 0.01910 0.01111 -0.0853 0.8287 0.1283 -8.000 -0.3797 0.01881 0.01072 -0.0837 0.8165 0.1338 -7.750 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-3.000 -0.0111 0.01481 0.00661 -0.0456 0.6388 0.3707 -2.750 0.0083 0.01458 0.00647 -0.0438 0.6324 0.3999 -2.500 0.0209 0.01439 0.00648 -0.0407 0.6244 0.4352 -2.250 0.0340 0.01413 0.00640 -0.0376 0.6171 0.4808 -2.000 0.0474 0.01390 0.00634 -0.0345 0.6108 0.5367 -1.500 0.0901 0.01329 0.00636 -0.0313 0.5960 0.6818 -1.250 0.2108 0.01371 0.00711 -0.0495 0.5853 0.7795 -1.000 0.2739 0.01441 0.00777 -0.0557 0.5767 0.8121 -0.750 0.3110 0.01495 0.00822 -0.0568 0.5699 0.8352 -0.500 0.3377 0.01540 0.00866 -0.0559 0.5625 0.8554 -0.250 0.3743 0.01591 0.00904 -0.0569 0.5559 0.8678 0.000 0.4074 0.01638 0.00944 -0.0574 0.5494 0.8806 0.250 0.4364 0.01679 0.00981 -0.0572 0.5423 0.8941 0.500 0.4807 0.01722 0.01012 -0.0601 0.5361 0.9021 0.750 0.5188 0.01769 0.01052 -0.0617 0.5297 0.9129 1.000 0.5552 0.01813 0.01093 -0.0630 0.5228 0.9254 1.250 0.6081 0.01841 0.01109 -0.0677 0.5166 0.9324 1.500 0.6463 0.01870 0.01133 -0.0697 0.5108 0.9419 1.750 0.6867 0.01884 0.01145 -0.0722 0.5041 0.9502 2.000 0.7310 0.01889 0.01141 -0.0755 0.4984 0.9580 2.250 0.7768 0.01904 0.01149 -0.0792 0.4928 0.9689 2.500 0.8245 0.01901 0.01148 -0.0833 0.4863 0.9805 2.750 0.8739 0.01862 0.01101 -0.0879 0.4805 0.9880 3.000 0.9195 0.01838 0.01066 -0.0919 0.4753 0.9956 3.250 0.9527 0.01815 0.01050 -0.0935 0.4699 1.0000 3.500 0.9700 0.01825 0.01059 -0.0919 0.4652 1.0000 3.750 0.9890 0.01835 0.01062 -0.0905 0.4608 1.0000 4.000 1.0086 0.01856 0.01076 -0.0893 0.4565 1.0000 4.250 1.0232 0.01868 0.01097 -0.0871 0.4509 1.0000 4.500 1.0411 0.01881 0.01108 -0.0855 0.4460 1.0000 4.750 1.0612 0.01896 0.01116 -0.0843 0.4418 1.0000 5.000 1.0809 0.01922 0.01139 -0.0830 0.4376 1.0000 5.250 1.0961 0.01944 0.01170 -0.0809 0.4331 1.0000 5.500 1.1139 0.01964 0.01192 -0.0792 0.4287 1.0000 5.750 1.1337 0.01982 0.01207 -0.0779 0.4247 1.0000 6.000 1.1571 0.02012 0.01224 -0.0773 0.4205 1.0000 6.250 1.1695 0.02037 0.01264 -0.0747 0.4162 1.0000 6.500 1.1853 0.02061 0.01294 -0.0727 0.4116 1.0000 6.750 1.2042 0.02084 0.01316 -0.0712 0.4077 1.0000 7.000 1.2256 0.02109 0.01336 -0.0702 0.4042 1.0000 7.250 1.2445 0.02148 0.01376 -0.0688 0.4007 1.0000 7.500 1.2565 0.02184 0.01424 -0.0662 0.3968 1.0000 7.750 1.2719 0.02215 0.01462 -0.0641 0.3928 1.0000 8.000 1.2901 0.02241 0.01487 -0.0626 0.3891 1.0000 8.250 1.3127 0.02265 0.01503 -0.0618 0.3852 1.0000 8.500 1.3238 0.02305 0.01553 -0.0590 0.3811 1.0000 8.750 1.3333 0.02341 0.01600 -0.0560 0.3769 1.0000 9.000 1.3476 0.02372 0.01634 -0.0537 0.3730 1.0000 9.250 1.3662 0.02395 0.01655 -0.0522 0.3694 1.0000 9.500 1.3911 0.02432 0.01685 -0.0520 0.3661 1.0000 9.750 1.3923 0.02484 0.01755 -0.0476 0.3627 1.0000 10.000 1.3973 0.02526 0.01808 -0.0438 0.3587 1.0000 10.250 1.4074 0.02556 0.01840 -0.0409 0.3548 1.0000 10.500 1.4244 0.02574 0.01855 -0.0392 0.3510 1.0000 10.750 1.4390 0.02617 0.01899 -0.0372 0.3475 1.0000 11.000 1.4276 0.02668 0.01965 -0.0307 0.3440 1.0000 11.250 1.4205 0.02707 0.02013 -0.0249 0.3403 1.0000 11.500 1.4236 0.02735 0.02043 -0.0210 0.3365 1.0000 11.750 1.4404 0.02753 0.02056 -0.0193 0.3327 1.0000 12.000 1.4347 0.02818 0.02130 -0.0144 0.3289 1.0000 12.250 1.4218 0.02902 0.02227 -0.0088 0.3249 1.0000 12.500 1.4210 0.02965 0.02296 -0.0052 0.3206 1.0000 12.750 1.4332 0.02991 0.02315 -0.0032 0.3160 1.0000 13.000 1.4288 0.03090 0.02424 0.0005 0.3118 1.0000 13.250 1.4159 0.03227 0.02576 0.0047 0.3071 1.0000 13.500 1.4162 0.03320 0.02672 0.0074 0.3024 1.0000 13.750 1.4334 0.03344 0.02687 0.0086 0.2975 1.0000 14.000 1.4108 0.03572 0.02936 0.0127 0.2924 1.0000 14.250 1.4039 0.03732 0.03103 0.0153 0.2867 1.0000 14.500 1.4142 0.03793 0.03155 0.0167 0.2808 1.0000 14.750 1.3921 0.04087 0.03469 0.0195 0.2746 1.0000 15.000 1.3898 0.04251 0.03634 0.0212 0.2681 1.0000 15.250 1.3810 0.04484 0.03873 0.0229 0.2613 1.0000 15.500 1.3690 0.04760 0.04156 0.0244 0.2536 1.0000 15.750 1.3610 0.05015 0.04413 0.0255 0.2457 1.0000 16.000 1.3502 0.05311 0.04711 0.0265 0.2369 1.0000 16.250 1.3350 0.05672 0.05078 0.0273 0.2276 1.0000 16.500 1.3326 0.05898 0.05292 0.0281 0.2188 1.0000 16.750 1.3137 0.06333 0.05738 0.0284 0.2097 1.0000 17.000 1.3097 0.06598 0.05997 0.0289 0.2022 1.0000 17.250 1.2972 0.06979 0.06382 0.0290 0.1944 1.0000 17.500 1.2958 0.07225 0.06622 0.0293 0.1882 1.0000 17.750 1.2855 0.07598 0.07003 0.0292 0.1820 1.0000 18.000 1.2904 0.07766 0.07158 0.0297 0.1765 1.0000 18.250 1.2788 0.08173 0.07577 0.0293 0.1714 1.0000 18.500 1.2763 0.08458 0.07863 0.0292 0.1667 1.0000 18.750 1.2815 0.08629 0.08024 0.0295 0.1619 1.0000 19.000 1.2713 0.09029 0.08437 0.0290 0.1575 1.0000 19.250 1.2707 0.09290 0.08697 0.0288 0.1530 1.0000