XFOIL Version 6.96 Calculated polar for: GOE 650 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.7347 0.12697 0.12461 -0.0498 1.0000 0.0230 -18.250 -0.7560 0.11930 0.11684 -0.0539 1.0000 0.0233 -18.000 -0.7740 0.11244 0.10989 -0.0575 1.0000 0.0235 -17.750 -0.7891 0.10627 0.10364 -0.0608 1.0000 0.0239 -17.500 -0.8017 0.10077 0.09806 -0.0636 1.0000 0.0240 -17.250 -0.8146 0.09522 0.09244 -0.0665 1.0000 0.0242 -17.000 -0.8241 0.09047 0.08762 -0.0689 1.0000 0.0243 -16.750 -0.8356 0.08540 0.08248 -0.0714 1.0000 0.0245 -16.500 -0.8470 0.08048 0.07749 -0.0739 1.0000 0.0246 -16.250 -0.8563 0.07608 0.07301 -0.0760 1.0000 0.0247 -16.000 -0.8668 0.07157 0.06844 -0.0782 1.0000 0.0248 -15.750 -0.8803 0.06726 0.06407 -0.0799 1.0000 0.0250 -15.500 -0.8933 0.06328 0.06005 -0.0813 1.0000 0.0253 -15.250 -0.9093 0.05909 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0.7059 0.2757 -0.500 0.4751 0.00685 0.00152 -0.1237 0.6990 0.2927 -0.250 0.5018 0.00681 0.00152 -0.1232 0.6907 0.3084 0.000 0.5279 0.00682 0.00154 -0.1226 0.6827 0.3220 0.250 0.5545 0.00680 0.00155 -0.1221 0.6734 0.3355 0.750 0.6056 0.00685 0.00159 -0.1207 0.6502 0.3601 1.000 0.6309 0.00689 0.00162 -0.1199 0.6349 0.3712 1.250 0.6548 0.00697 0.00165 -0.1189 0.6154 0.3823 1.500 0.6781 0.00707 0.00171 -0.1177 0.5918 0.3940 1.750 0.7000 0.00725 0.00178 -0.1163 0.5655 0.4039 2.000 0.7225 0.00741 0.00188 -0.1150 0.5439 0.4159 2.250 0.7454 0.00756 0.00199 -0.1139 0.5249 0.4273 2.500 0.7685 0.00772 0.00209 -0.1127 0.5070 0.4385 2.750 0.7916 0.00787 0.00221 -0.1116 0.4898 0.4508 3.000 0.8145 0.00802 0.00232 -0.1104 0.4716 0.4638 3.250 0.8370 0.00819 0.00245 -0.1092 0.4503 0.4783 3.500 0.8583 0.00839 0.00258 -0.1077 0.4262 0.4934 3.750 0.8786 0.00862 0.00274 -0.1061 0.3969 0.5127 4.000 0.8975 0.00888 0.00293 -0.1043 0.3670 0.5370 4.250 0.9161 0.00915 0.00314 -0.1024 0.3418 0.5659 4.500 0.9358 0.00934 0.00335 -0.1006 0.3243 0.5974 4.750 0.9548 0.00947 0.00353 -0.0988 0.3104 0.6402 5.000 0.9715 0.00948 0.00371 -0.0964 0.2992 0.7187 5.250 1.0421 0.00951 0.00416 -0.1060 0.2798 1.0000 5.500 1.0626 0.00977 0.00435 -0.1045 0.2673 1.0000 5.750 1.0814 0.01004 0.00455 -0.1026 0.2555 1.0000 6.000 1.1015 0.01024 0.00472 -0.1009 0.2464 1.0000 6.250 1.1204 0.01050 0.00492 -0.0991 0.2362 1.0000 6.500 1.1402 0.01073 0.00512 -0.0974 0.2278 1.0000 6.750 1.1597 0.01099 0.00534 -0.0957 0.2196 1.0000 7.000 1.1791 0.01126 0.00557 -0.0941 0.2110 1.0000 7.250 1.1987 0.01153 0.00580 -0.0925 0.2026 1.0000 7.500 1.2174 0.01185 0.00607 -0.0907 0.1933 1.0000 7.750 1.2372 0.01212 0.00633 -0.0892 0.1856 1.0000 8.000 1.2554 0.01248 0.00663 -0.0875 0.1768 1.0000 8.250 1.2753 0.01277 0.00691 -0.0860 0.1701 1.0000 8.500 1.2928 0.01317 0.00726 -0.0842 0.1612 1.0000 8.750 1.3121 0.01350 0.00758 -0.0828 0.1541 1.0000 9.000 1.3295 0.01393 0.00796 -0.0810 0.1461 1.0000 9.250 1.3482 0.01429 0.00832 -0.0795 0.1401 1.0000 9.500 1.3652 0.01476 0.00875 -0.0778 0.1330 1.0000 9.750 1.3834 0.01516 0.00914 -0.0763 0.1272 1.0000 10.000 1.3999 0.01567 0.00962 -0.0746 0.1210 1.0000 10.250 1.4180 0.01610 0.01006 -0.0732 0.1164 1.0000 10.500 1.4341 0.01665 0.01058 -0.0715 0.1107 1.0000 10.750 1.4510 0.01716 0.01109 -0.0700 0.1059 1.0000 11.000 1.4671 0.01772 0.01164 -0.0684 0.1007 1.0000 11.250 1.4821 0.01837 0.01227 -0.0667 0.0938 1.0000 11.500 1.4958 0.01909 0.01296 -0.0650 0.0870 1.0000 11.750 1.5094 0.01985 0.01369 -0.0633 0.0788 1.0000 12.000 1.5157 0.02109 0.01479 -0.0608 0.0610 1.0000 12.250 1.5134 0.02294 0.01647 -0.0576 0.0397 1.0000 12.500 1.5205 0.02421 0.01773 -0.0554 0.0352 1.0000 12.750 1.5312 0.02526 0.01881 -0.0538 0.0333 1.0000 13.000 1.5415 0.02637 0.01995 -0.0521 0.0319 1.0000 13.250 1.5501 0.02763 0.02125 -0.0505 0.0306 1.0000 13.500 1.5570 0.02904 0.02270 -0.0487 0.0295 1.0000 13.750 1.5674 0.03020 0.02393 -0.0474 0.0288 1.0000 14.000 1.5771 0.03147 0.02525 -0.0461 0.0281 1.0000 14.250 1.5850 0.03289 0.02672 -0.0447 0.0274 1.0000 14.500 1.5917 0.03445 0.02834 -0.0434 0.0268 1.0000 14.750 1.5960 0.03626 0.03022 -0.0421 0.0261 1.0000 15.000 1.5975 0.03840 0.03242 -0.0407 0.0255 1.0000 15.250 1.6016 0.04034 0.03443 -0.0396 0.0249 1.0000 15.500 1.6077 0.04215 0.03631 -0.0387 0.0246 1.0000 15.750 1.6127 0.04411 0.03835 -0.0379 0.0242 1.0000 16.000 1.6161 0.04629 0.04060 -0.0371 0.0237 1.0000 16.250 1.6185 0.04860 0.04298 -0.0365 0.0232 1.0000 16.500 1.6189 0.05120 0.04566 -0.0359 0.0229 1.0000 16.750 1.6170 0.05415 0.04868 -0.0355 0.0225 1.0000 17.000 1.6120 0.05756 0.05218 -0.0353 0.0221 1.0000 17.250 1.6035 0.06151 0.05623 -0.0353 0.0218 1.0000 17.500 1.5917 0.06602 0.06085 -0.0356 0.0214 1.0000 17.750 1.5898 0.06937 0.06429 -0.0360 0.0212 1.0000 18.000 1.5860 0.07304 0.06805 -0.0364 0.0210 1.0000 18.250 1.5818 0.07677 0.07188 -0.0370 0.0207 1.0000 18.500 1.5763 0.08072 0.07593 -0.0377 0.0204 1.0000 18.750 1.5656 0.08550 0.08081 -0.0388 0.0202 1.0000 19.000 1.5538 0.09051 0.08593 -0.0400 0.0200 1.0000 19.250 1.5409 0.09572 0.09124 -0.0415 0.0198 1.0000