XFOIL Version 6.96 Calculated polar for: GOE 648 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 ------ -------- --------- --------- -------- -------- -------- -18.250 -0.8354 0.09913 0.09631 -0.0609 1.0000 0.0149 -18.000 -0.9304 0.08061 0.07753 -0.0721 1.0000 0.0146 -17.750 -1.0244 0.06337 0.05998 -0.0828 1.0000 0.0143 -17.500 -1.0788 0.05212 0.04849 -0.0900 1.0000 0.0142 -17.250 -1.1111 0.04444 0.04063 -0.0950 1.0000 0.0142 -17.000 -1.1307 0.03908 0.03513 -0.0980 1.0000 0.0143 -16.750 -1.1435 0.03508 0.03102 -0.0998 1.0000 0.0144 -16.500 -1.1530 0.03197 0.02780 -0.1004 1.0000 0.0146 -16.250 -1.1610 0.02958 0.02533 -0.0999 1.0000 0.0147 -16.000 -1.1698 0.02770 0.02337 -0.0981 1.0000 0.0149 -15.750 -1.1713 0.02624 0.02182 -0.0966 0.9996 0.0151 -15.500 -1.1543 0.02495 0.02046 -0.0974 0.9979 0.0154 -15.250 -1.1356 0.02390 0.01934 -0.0978 0.9956 0.0157 -15.000 -1.1149 0.02302 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0.2378 -0.500 0.3664 0.00928 0.00211 -0.0732 0.3282 0.2616 -0.250 0.3913 0.00927 0.00214 -0.0725 0.3207 0.2860 0.000 0.4159 0.00928 0.00218 -0.0717 0.3134 0.3105 0.250 0.4409 0.00923 0.00221 -0.0710 0.3087 0.3439 0.500 0.4657 0.00919 0.00224 -0.0703 0.3045 0.3773 0.750 0.4897 0.00914 0.00230 -0.0694 0.2996 0.4221 1.000 0.5133 0.00910 0.00237 -0.0685 0.2945 0.4735 1.250 0.5380 0.00906 0.00244 -0.0677 0.2912 0.5137 1.500 0.5630 0.00908 0.00250 -0.0670 0.2872 0.5382 1.750 0.5875 0.00912 0.00258 -0.0661 0.2829 0.5632 2.000 0.6116 0.00917 0.00266 -0.0653 0.2786 0.5872 2.250 0.6351 0.00914 0.00274 -0.0642 0.2760 0.6268 2.500 0.6579 0.00909 0.00284 -0.0631 0.2735 0.6759 2.750 0.6805 0.00907 0.00294 -0.0619 0.2706 0.7193 3.000 0.7034 0.00910 0.00303 -0.0607 0.2671 0.7526 3.250 0.7260 0.00915 0.00314 -0.0595 0.2640 0.7790 3.500 0.7481 0.00921 0.00324 -0.0582 0.2607 0.8053 3.750 0.7696 0.00920 0.00335 -0.0567 0.2585 0.8402 4.000 0.8050 0.00914 0.00352 -0.0582 0.2553 0.9181 4.250 0.9089 0.00949 0.00384 -0.0749 0.2490 0.9795 4.500 0.9408 0.00971 0.00402 -0.0758 0.2448 0.9994 4.750 0.9657 0.00985 0.00414 -0.0752 0.2420 1.0000 5.000 0.9877 0.00997 0.00426 -0.0739 0.2392 1.0000 5.250 1.0094 0.01010 0.00438 -0.0726 0.2363 1.0000 5.500 1.0307 0.01026 0.00451 -0.0713 0.2331 1.0000 5.750 1.0516 0.01043 0.00466 -0.0699 0.2295 1.0000 6.000 1.0720 0.01059 0.00481 -0.0684 0.2262 1.0000 6.250 1.0918 0.01073 0.00495 -0.0667 0.2226 1.0000 6.500 1.1108 0.01090 0.00509 -0.0650 0.2184 1.0000 6.750 1.1289 0.01112 0.00527 -0.0631 0.2129 1.0000 7.000 1.1486 0.01130 0.00544 -0.0615 0.2083 1.0000 7.250 1.1681 0.01150 0.00563 -0.0599 0.2037 1.0000 7.500 1.1871 0.01174 0.00584 -0.0583 0.1989 1.0000 7.750 1.2068 0.01196 0.00606 -0.0569 0.1946 1.0000 8.000 1.2266 0.01220 0.00628 -0.0554 0.1900 1.0000 8.250 1.2454 0.01248 0.00654 -0.0539 0.1850 1.0000 8.500 1.2651 0.01275 0.00680 -0.0526 0.1811 1.0000 8.750 1.2847 0.01302 0.00707 -0.0512 0.1770 1.0000 9.000 1.3030 0.01336 0.00738 -0.0497 0.1717 1.0000 9.250 1.3218 0.01369 0.00770 -0.0484 0.1672 1.0000 9.500 1.3407 0.01402 0.00803 -0.0470 0.1629 1.0000 9.750 1.3587 0.01440 0.00840 -0.0456 0.1585 1.0000 10.000 1.3767 0.01479 0.00879 -0.0442 0.1548 1.0000 10.250 1.3958 0.01514 0.00915 -0.0431 0.1522 1.0000 10.500 1.4141 0.01553 0.00955 -0.0418 0.1489 1.0000 10.750 1.4316 0.01597 0.00999 -0.0405 0.1459 1.0000 11.000 1.4482 0.01647 0.01049 -0.0391 0.1423 1.0000 11.250 1.4663 0.01689 0.01094 -0.0380 0.1397 1.0000 11.500 1.4833 0.01738 0.01144 -0.0367 0.1363 1.0000 11.750 1.4987 0.01798 0.01204 -0.0354 0.1323 1.0000 12.000 1.5140 0.01860 0.01266 -0.0340 0.1285 1.0000 12.250 1.5303 0.01916 0.01325 -0.0329 0.1258 1.0000 12.500 1.5445 0.01987 0.01396 -0.0316 0.1212 1.0000 12.750 1.5573 0.02068 0.01477 -0.0302 0.1170 1.0000 13.000 1.5697 0.02153 0.01561 -0.0288 0.1107 1.0000 13.250 1.5801 0.02254 0.01661 -0.0273 0.1051 1.0000 13.500 1.5885 0.02371 0.01776 -0.0258 0.0973 1.0000 13.750 1.5976 0.02486 0.01891 -0.0245 0.0915 1.0000 14.000 1.5997 0.02655 0.02056 -0.0227 0.0806 1.0000 14.250 1.5998 0.02847 0.02243 -0.0210 0.0708 1.0000 14.500 1.6001 0.03045 0.02440 -0.0195 0.0638 1.0000 14.750 1.6005 0.03251 0.02648 -0.0183 0.0590 1.0000 15.000 1.6031 0.03448 0.02848 -0.0173 0.0560 1.0000 15.250 1.6048 0.03660 0.03065 -0.0165 0.0537 1.0000 15.500 1.6085 0.03862 0.03272 -0.0159 0.0520 1.0000 15.750 1.6121 0.04073 0.03489 -0.0154 0.0509 1.0000 16.000 1.6117 0.04330 0.03752 -0.0150 0.0492 1.0000 16.250 1.6129 0.04578 0.04006 -0.0148 0.0486 1.0000 16.500 1.6115 0.04860 0.04295 -0.0147 0.0475 1.0000 16.750 1.6107 0.05145 0.04588 -0.0148 0.0467 1.0000 17.000 1.6097 0.05437 0.04888 -0.0149 0.0459 1.0000 17.250 1.6075 0.05748 0.05207 -0.0152 0.0455 1.0000 17.500 1.6027 0.06098 0.05565 -0.0156 0.0448 1.0000 17.750 1.5956 0.06482 0.05959 -0.0162 0.0441 1.0000 18.000 1.5861 0.06903 0.06389 -0.0170 0.0434 1.0000 18.250 1.5759 0.07339 0.06835 -0.0179 0.0430 1.0000 18.500 1.5620 0.07836 0.07341 -0.0191 0.0424 1.0000 18.750 1.5474 0.08351 0.07868 -0.0205 0.0421 1.0000 19.000 1.5294 0.08921 0.08448 -0.0221 0.0415 1.0000 19.250 1.5116 0.09499 0.09037 -0.0238 0.0408 1.0000