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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.7536 0.11996 0.11747 -0.0491 1.0000 0.0186 -18.500 -0.7967 0.10831 0.10566 -0.0556 1.0000 0.0188 -18.250 -0.8228 0.10026 0.09751 -0.0601 1.0000 0.0188 -18.000 -0.8524 0.09176 0.08889 -0.0649 1.0000 0.0189 -17.750 -0.8845 0.08319 0.08019 -0.0699 1.0000 0.0190 -17.500 -0.9145 0.07540 0.07228 -0.0743 1.0000 0.0190 -17.250 -0.9449 0.06774 0.06450 -0.0787 1.0000 0.0191 -17.000 -0.9755 0.06027 0.05690 -0.0830 1.0000 0.0191 -16.750 -0.9965 0.05405 0.05055 -0.0866 1.0000 0.0191 -16.500 -1.0217 0.04750 0.04387 -0.0905 1.0000 0.0191 -16.250 -1.0460 0.04147 0.03770 -0.0939 1.0000 0.0193 -16.000 -1.0624 0.03691 0.03303 -0.0961 1.0000 0.0194 -15.750 -1.0781 0.03304 0.02905 -0.0972 1.0000 0.0196 -15.500 -1.0894 0.03035 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0.9234 0.00944 0.00399 -0.0783 0.2755 1.0000 4.500 0.9450 0.00956 0.00409 -0.0769 0.2721 1.0000 4.750 0.9659 0.00972 0.00422 -0.0755 0.2689 1.0000 5.000 0.9859 0.00991 0.00438 -0.0739 0.2649 1.0000 5.250 1.0079 0.01004 0.00450 -0.0726 0.2624 1.0000 5.500 1.0304 0.01014 0.00462 -0.0715 0.2601 1.0000 5.750 1.0524 0.01027 0.00474 -0.0703 0.2570 1.0000 6.000 1.0734 0.01043 0.00488 -0.0689 0.2534 1.0000 6.250 1.0919 0.01062 0.00505 -0.0670 0.2499 1.0000 6.500 1.1106 0.01080 0.00521 -0.0652 0.2464 1.0000 6.750 1.1318 0.01091 0.00534 -0.0638 0.2438 1.0000 7.000 1.1523 0.01105 0.00548 -0.0624 0.2402 1.0000 7.250 1.1718 0.01124 0.00565 -0.0608 0.2364 1.0000 7.500 1.1897 0.01151 0.00588 -0.0589 0.2316 1.0000 7.750 1.2120 0.01163 0.00603 -0.0579 0.2281 1.0000 8.000 1.2329 0.01182 0.00621 -0.0566 0.2239 1.0000 8.250 1.2523 0.01206 0.00643 -0.0552 0.2194 1.0000 8.500 1.2718 0.01232 0.00668 -0.0538 0.2150 1.0000 8.750 1.2931 0.01252 0.00690 -0.0527 0.2113 1.0000 9.000 1.3128 0.01278 0.00715 -0.0513 0.2067 1.0000 9.250 1.3308 0.01313 0.00747 -0.0498 0.2014 1.0000 9.500 1.3517 0.01337 0.00773 -0.0487 0.1983 1.0000 9.750 1.3712 0.01367 0.00803 -0.0475 0.1936 1.0000 10.000 1.3888 0.01406 0.00839 -0.0460 0.1885 1.0000 10.250 1.4080 0.01440 0.00874 -0.0448 0.1847 1.0000 10.500 1.4269 0.01475 0.00910 -0.0436 0.1808 1.0000 10.750 1.4441 0.01519 0.00953 -0.0422 0.1761 1.0000 11.000 1.4608 0.01566 0.01000 -0.0408 0.1719 1.0000 11.250 1.4796 0.01604 0.01041 -0.0396 0.1685 1.0000 11.500 1.4968 0.01651 0.01088 -0.0384 0.1650 1.0000 11.750 1.5119 0.01710 0.01146 -0.0369 0.1608 1.0000 12.000 1.5287 0.01761 0.01200 -0.0357 0.1575 1.0000 12.250 1.5460 0.01811 0.01253 -0.0346 0.1548 1.0000 12.500 1.5615 0.01871 0.01314 -0.0333 0.1511 1.0000 12.750 1.5749 0.01945 0.01388 -0.0319 0.1473 1.0000 13.000 1.5905 0.02009 0.01454 -0.0307 0.1439 1.0000 13.250 1.6058 0.02075 0.01523 -0.0296 0.1403 1.0000 13.500 1.6184 0.02159 0.01608 -0.0283 0.1364 1.0000 13.750 1.6304 0.02249 0.01700 -0.0270 0.1324 1.0000 14.000 1.6448 0.02326 0.01780 -0.0261 0.1290 1.0000 14.250 1.6541 0.02439 0.01891 -0.0247 0.1233 1.0000 14.500 1.6653 0.02541 0.01997 -0.0236 0.1200 1.0000 14.750 1.6757 0.02652 0.02110 -0.0225 0.1149 1.0000 15.000 1.6815 0.02800 0.02257 -0.0212 0.1095 1.0000 15.250 1.6896 0.02935 0.02394 -0.0201 0.1038 1.0000 15.500 1.6920 0.03118 0.02576 -0.0189 0.0969 1.0000 15.750 1.6909 0.03339 0.02795 -0.0176 0.0888 1.0000 16.000 1.6836 0.03623 0.03075 -0.0164 0.0777 1.0000 16.250 1.6760 0.03926 0.03378 -0.0154 0.0702 1.0000 16.500 1.6727 0.04204 0.03660 -0.0149 0.0664 1.0000 16.750 1.6649 0.04537 0.03996 -0.0145 0.0625 1.0000 17.000 1.6619 0.04832 0.04298 -0.0143 0.0607 1.0000 17.250 1.6558 0.05172 0.04645 -0.0144 0.0590 1.0000 17.500 1.6463 0.05559 0.05039 -0.0146 0.0573 1.0000 17.750 1.6356 0.05970 0.05458 -0.0150 0.0557 1.0000 18.000 1.6300 0.06330 0.05828 -0.0155 0.0550 1.0000 18.250 1.6212 0.06737 0.06245 -0.0162 0.0544 1.0000 18.500 1.6089 0.07193 0.06712 -0.0171 0.0536 1.0000 18.750 1.5943 0.07692 0.07220 -0.0182 0.0528 1.0000 19.000 1.5784 0.08219 0.07758 -0.0196 0.0523 1.0000 19.250 1.5596 0.08792 0.08342 -0.0212 0.0518 1.0000