XFOIL Version 6.96 Calculated polar for: GOE 735 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9685 0.09799 0.09488 -0.0399 1.0000 0.0283 -19.500 -1.0758 0.07901 0.07557 -0.0514 1.0000 0.0280 -19.250 -1.1656 0.06273 0.05896 -0.0616 1.0000 0.0277 -18.750 -1.2271 0.04650 0.04234 -0.0728 0.9597 0.0281 -18.500 -1.1821 0.04106 0.03651 -0.0866 0.8691 0.0287 -18.250 -1.1936 0.03803 0.03322 -0.0866 0.8248 0.0288 -17.750 -1.2046 0.03316 0.02805 -0.0858 0.7900 0.0292 -17.500 -1.2045 0.03139 0.02616 -0.0850 0.7797 0.0297 -17.250 -1.2035 0.02979 0.02446 -0.0838 0.7700 0.0299 -17.000 -1.2003 0.02844 0.02301 -0.0824 0.7620 0.0301 -16.750 -1.1983 0.02708 0.02157 -0.0807 0.7541 0.0305 -16.500 -1.1953 0.02588 0.02028 -0.0788 0.7465 0.0309 -16.250 -1.1904 0.02481 0.01914 -0.0769 0.7404 0.0312 -16.000 -1.1838 0.02388 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0.00287 -0.0141 0.3859 0.1308 -1.500 0.0994 0.01026 0.00284 -0.0137 0.3824 0.1360 -1.250 0.1266 0.01025 0.00282 -0.0135 0.3790 0.1406 -1.000 0.1533 0.01022 0.00280 -0.0131 0.3755 0.1470 -0.750 0.1800 0.01021 0.00280 -0.0128 0.3721 0.1542 -0.500 0.2071 0.01016 0.00278 -0.0125 0.3699 0.1625 -0.250 0.2341 0.01013 0.00278 -0.0122 0.3671 0.1714 0.000 0.2605 0.01008 0.00277 -0.0118 0.3638 0.1841 0.250 0.2866 0.01005 0.00278 -0.0114 0.3600 0.2014 0.500 0.3120 0.01000 0.00280 -0.0109 0.3564 0.2257 0.750 0.3374 0.00992 0.00281 -0.0104 0.3539 0.2548 1.000 0.3633 0.00985 0.00283 -0.0099 0.3518 0.2834 1.250 0.3886 0.00976 0.00286 -0.0094 0.3493 0.3177 1.500 0.4138 0.00970 0.00289 -0.0088 0.3466 0.3502 1.750 0.4385 0.00964 0.00293 -0.0082 0.3437 0.3856 2.000 0.4623 0.00957 0.00297 -0.0074 0.3408 0.4286 2.250 0.4823 0.00937 0.00302 -0.0060 0.3374 0.5133 2.500 0.5040 0.00919 0.00306 -0.0047 0.3356 0.5823 2.750 0.5249 0.00905 0.00311 -0.0033 0.3334 0.6413 3.000 0.5407 0.00880 0.00316 -0.0008 0.3311 0.7304 3.250 0.5575 0.00864 0.00325 0.0016 0.3289 0.8060 3.500 0.5807 0.00861 0.00338 0.0026 0.3263 0.8579 3.750 0.6168 0.00870 0.00359 0.0010 0.3234 0.9041 4.000 0.6599 0.00889 0.00380 -0.0022 0.3204 0.9274 4.250 0.7028 0.00906 0.00398 -0.0054 0.3186 0.9379 4.500 0.7321 0.00921 0.00413 -0.0057 0.3163 0.9489 4.750 0.7738 0.00940 0.00430 -0.0087 0.3134 0.9517 5.000 0.8089 0.00960 0.00448 -0.0103 0.3107 0.9556 5.250 0.8339 0.00981 0.00467 -0.0098 0.3084 0.9626 5.500 0.8661 0.01004 0.00488 -0.0108 0.3056 0.9656 5.750 0.9002 0.01024 0.00507 -0.0123 0.3033 0.9669 6.000 0.9337 0.01040 0.00523 -0.0137 0.3014 0.9683 6.250 0.9660 0.01058 0.00540 -0.0148 0.2992 0.9701 6.500 0.9961 0.01076 0.00558 -0.0155 0.2966 0.9723 6.750 1.0224 0.01097 0.00577 -0.0156 0.2936 0.9751 7.000 1.0433 0.01122 0.00600 -0.0145 0.2906 0.9789 7.250 1.0748 0.01146 0.00623 -0.0157 0.2875 0.9798 7.500 1.1063 0.01163 0.00641 -0.0168 0.2857 0.9807 7.750 1.1369 0.01183 0.00662 -0.0178 0.2838 0.9819 8.000 1.1670 0.01205 0.00684 -0.0187 0.2817 0.9833 8.250 1.1957 0.01229 0.00709 -0.0194 0.2792 0.9851 8.500 1.2222 0.01257 0.00736 -0.0197 0.2767 0.9872 8.750 1.2433 0.01290 0.00767 -0.0191 0.2738 0.9902 9.000 1.2660 0.01318 0.00798 -0.0188 0.2718 0.9924 9.250 1.2944 0.01341 0.00822 -0.0196 0.2704 0.9938 9.500 1.3217 0.01368 0.00851 -0.0203 0.2686 0.9954 9.750 1.3483 0.01399 0.00886 -0.0210 0.2666 0.9972 10.000 1.3737 0.01439 0.00926 -0.0217 0.2641 0.9987 10.250 1.3988 0.01487 0.00975 -0.0225 0.2615 0.9998 10.500 1.4038 0.01548 0.01038 -0.0197 0.2592 1.0000 10.750 1.4074 0.01618 0.01109 -0.0168 0.2570 1.0000 11.000 1.4172 0.01673 0.01168 -0.0148 0.2555 1.0000 11.250 1.4273 0.01733 0.01232 -0.0130 0.2539 1.0000 11.500 1.4375 0.01799 0.01301 -0.0113 0.2520 1.0000 11.750 1.4471 0.01873 0.01377 -0.0096 0.2499 1.0000 12.000 1.4559 0.01957 0.01463 -0.0080 0.2477 1.0000 12.250 1.4636 0.02053 0.01560 -0.0065 0.2453 1.0000 12.500 1.4703 0.02160 0.01669 -0.0049 0.2428 1.0000 12.750 1.4808 0.02248 0.01761 -0.0038 0.2411 1.0000 13.000 1.4918 0.02337 0.01853 -0.0028 0.2388 1.0000 13.250 1.4999 0.02446 0.01965 -0.0016 0.2349 1.0000 13.500 1.5039 0.02589 0.02108 -0.0004 0.2311 1.0000 13.750 1.5061 0.02749 0.02269 0.0009 0.2276 1.0000 14.000 1.5150 0.02865 0.02389 0.0017 0.2241 1.0000 14.250 1.5169 0.03038 0.02563 0.0027 0.2188 1.0000 14.500 1.5161 0.03242 0.02769 0.0037 0.2148 1.0000 14.750 1.5204 0.03412 0.02942 0.0043 0.2105 1.0000 15.000 1.5236 0.03598 0.03132 0.0049 0.2071 1.0000 15.250 1.5195 0.03855 0.03390 0.0055 0.2021 1.0000 15.500 1.5190 0.04086 0.03624 0.0059 0.1988 1.0000 15.750 1.5181 0.04324 0.03865 0.0063 0.1936 1.0000 16.000 1.5134 0.04605 0.04149 0.0066 0.1899 1.0000 16.250 1.5040 0.04939 0.04485 0.0068 0.1850 1.0000 16.500 1.5035 0.05188 0.04739 0.0069 0.1821 1.0000 16.750 1.4968 0.05503 0.05057 0.0070 0.1777 1.0000 17.000 1.4833 0.05897 0.05454 0.0069 0.1735 1.0000 17.250 1.4814 0.06175 0.05737 0.0068 0.1710 1.0000 17.500 1.4738 0.06515 0.06081 0.0066 0.1661 1.0000 17.750 1.4588 0.06946 0.06515 0.0062 0.1620 1.0000 18.000 1.4541 0.07266 0.06840 0.0059 0.1598 1.0000 18.250 1.4510 0.07572 0.07150 0.0055 0.1565 1.0000 18.500 1.4362 0.08019 0.07600 0.0048 0.1517 1.0000 18.750 1.4283 0.08387 0.07971 0.0042 0.1488 1.0000 19.000 1.4250 0.08707 0.08298 0.0036 0.1468 1.0000 19.250 1.4205 0.09044 0.08638 0.0029 0.1427 1.0000