XFOIL Version 6.96 Calculated polar for: GOE 601 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9503 0.09903 0.09590 -0.0674 1.0000 0.0199 -19.500 -0.9608 0.09404 0.09083 -0.0699 1.0000 0.0201 -19.250 -0.9697 0.08923 0.08597 -0.0723 1.0000 0.0203 -19.000 -0.9794 0.08445 0.08112 -0.0747 1.0000 0.0205 -18.750 -0.9882 0.07988 0.07648 -0.0769 1.0000 0.0206 -18.500 -0.9966 0.07542 0.07195 -0.0790 1.0000 0.0208 -18.250 -1.0035 0.07127 0.06772 -0.0809 1.0000 0.0210 -18.000 -1.0099 0.06728 0.06366 -0.0826 1.0000 0.0212 -17.750 -1.0192 0.06315 0.05945 -0.0842 1.0000 0.0213 -17.500 -1.0231 0.05969 0.05592 -0.0856 1.0000 0.0216 -17.250 -1.0304 0.05615 0.05229 -0.0867 1.0000 0.0217 -17.000 -1.0351 0.05297 0.04903 -0.0876 1.0000 0.0219 -16.750 -1.0385 0.05007 0.04605 -0.0882 1.0000 0.0222 -16.500 -1.0392 0.04753 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0.00178 -0.0712 0.7324 0.3960 -2.000 0.0873 0.00681 0.00175 -0.0706 0.7273 0.4298 -1.750 0.1133 0.00677 0.00173 -0.0701 0.7226 0.4498 -1.500 0.1397 0.00673 0.00172 -0.0698 0.7177 0.4648 -1.250 0.1656 0.00668 0.00170 -0.0693 0.7118 0.4791 -1.000 0.1914 0.00666 0.00167 -0.0688 0.7058 0.4903 -0.750 0.2182 0.00665 0.00167 -0.0685 0.7005 0.5003 -0.500 0.2439 0.00660 0.00165 -0.0680 0.6940 0.5092 -0.250 0.2695 0.00662 0.00163 -0.0675 0.6867 0.5170 0.000 0.2955 0.00658 0.00162 -0.0670 0.6794 0.5246 0.250 0.3206 0.00659 0.00161 -0.0664 0.6717 0.5326 0.500 0.3463 0.00657 0.00161 -0.0659 0.6639 0.5408 0.750 0.3708 0.00658 0.00161 -0.0651 0.6552 0.5501 1.000 0.3959 0.00656 0.00162 -0.0645 0.6464 0.5609 1.250 0.4197 0.00659 0.00164 -0.0636 0.6368 0.5727 1.500 0.4442 0.00657 0.00166 -0.0628 0.6270 0.5856 1.750 0.4671 0.00657 0.00169 -0.0618 0.6160 0.6026 2.000 0.4886 0.00659 0.00173 -0.0604 0.6027 0.6265 2.250 0.5096 0.00659 0.00178 -0.0589 0.5882 0.6536 2.750 0.5489 0.00664 0.00192 -0.0554 0.5556 0.7124 3.000 0.5656 0.00669 0.00201 -0.0529 0.5358 0.7471 3.250 0.5800 0.00677 0.00212 -0.0500 0.5095 0.7854 3.500 0.5881 0.00693 0.00227 -0.0458 0.4732 0.8271 3.750 0.5926 0.00722 0.00250 -0.0409 0.4215 0.8747 4.000 0.6122 0.00772 0.00286 -0.0395 0.3666 0.9219 4.250 0.6588 0.00823 0.00324 -0.0440 0.3335 0.9475 4.500 0.7095 0.00865 0.00356 -0.0494 0.3132 0.9603 4.750 0.7492 0.00899 0.00383 -0.0522 0.3000 0.9705 5.000 0.7826 0.00925 0.00406 -0.0536 0.2910 0.9792 5.250 0.8166 0.00952 0.00429 -0.0551 0.2826 0.9848 5.500 0.8515 0.00975 0.00449 -0.0569 0.2749 0.9895 5.750 0.8837 0.01003 0.00472 -0.0581 0.2662 0.9942 6.000 0.9200 0.01025 0.00491 -0.0602 0.2574 0.9975 6.250 0.9558 0.01051 0.00513 -0.0622 0.2484 0.9996 6.500 0.9699 0.01064 0.00525 -0.0596 0.2421 1.0000 6.750 0.9770 0.01083 0.00540 -0.0556 0.2355 1.0000 7.000 0.9894 0.01098 0.00556 -0.0526 0.2291 1.0000 7.250 0.9995 0.01124 0.00576 -0.0492 0.2188 1.0000 7.500 1.0120 0.01150 0.00598 -0.0464 0.2070 1.0000 7.750 1.0234 0.01185 0.00626 -0.0435 0.1923 1.0000 8.000 1.0317 0.01237 0.00664 -0.0401 0.1688 1.0000 8.250 1.0307 0.01332 0.00732 -0.0353 0.1254 1.0000 8.500 1.0140 0.01513 0.00867 -0.0285 0.0515 1.0000 8.750 1.0237 0.01587 0.00933 -0.0258 0.0390 1.0000 9.000 1.0385 0.01640 0.00985 -0.0240 0.0358 1.0000 9.250 1.0533 0.01695 0.01040 -0.0222 0.0342 1.0000 9.500 1.0674 0.01757 0.01103 -0.0204 0.0324 1.0000 9.750 1.0833 0.01810 0.01159 -0.0189 0.0318 1.0000 10.000 1.0991 0.01866 0.01218 -0.0175 0.0311 1.0000 10.250 1.1142 0.01928 0.01282 -0.0160 0.0304 1.0000 10.500 1.1287 0.01996 0.01352 -0.0145 0.0296 1.0000 10.750 1.1416 0.02075 0.01434 -0.0129 0.0289 1.0000 11.000 1.1535 0.02162 0.01525 -0.0113 0.0283 1.0000 11.250 1.1634 0.02266 0.01634 -0.0095 0.0277 1.0000 11.500 1.1772 0.02346 0.01718 -0.0083 0.0274 1.0000 11.750 1.1906 0.02431 0.01807 -0.0070 0.0271 1.0000 12.000 1.2037 0.02519 0.01899 -0.0058 0.0266 1.0000 12.250 1.2151 0.02621 0.02006 -0.0046 0.0263 1.0000 12.500 1.2263 0.02727 0.02116 -0.0033 0.0259 1.0000 12.750 1.2365 0.02842 0.02235 -0.0021 0.0255 1.0000 13.000 1.2457 0.02966 0.02364 -0.0009 0.0250 1.0000 13.250 1.2539 0.03103 0.02505 0.0004 0.0247 1.0000 13.500 1.2597 0.03262 0.02669 0.0016 0.0243 1.0000 13.750 1.2622 0.03452 0.02865 0.0030 0.0240 1.0000 14.000 1.2569 0.03714 0.03136 0.0045 0.0235 1.0000 14.250 1.2621 0.03896 0.03324 0.0054 0.0234 1.0000 14.500 1.2728 0.04033 0.03467 0.0060 0.0232 1.0000 14.750 1.2809 0.04197 0.03636 0.0066 0.0229 1.0000 15.000 1.2858 0.04395 0.03841 0.0072 0.0227 1.0000 15.250 1.2891 0.04615 0.04068 0.0077 0.0225 1.0000 15.500 1.2941 0.04825 0.04284 0.0081 0.0221 1.0000 15.750 1.2964 0.05066 0.04532 0.0084 0.0219 1.0000 16.000 1.2989 0.05311 0.04783 0.0086 0.0216 1.0000 16.250 1.3021 0.05557 0.05035 0.0086 0.0213 1.0000 16.500 1.3015 0.05851 0.05335 0.0086 0.0210 1.0000 16.750 1.2995 0.06166 0.05657 0.0084 0.0210 1.0000 17.000 1.2987 0.06473 0.05970 0.0081 0.0207 1.0000 17.250 1.2959 0.06811 0.06314 0.0077 0.0204 1.0000 17.500 1.2892 0.07201 0.06711 0.0071 0.0202 1.0000 17.750 1.2760 0.07664 0.07182 0.0065 0.0198 1.0000 18.000 1.2747 0.08001 0.07527 0.0058 0.0197 1.0000 18.250 1.2740 0.08338 0.07872 0.0050 0.0196 1.0000 18.500 1.2740 0.08678 0.08221 0.0040 0.0195 1.0000 18.750 1.2724 0.09038 0.08589 0.0029 0.0193 1.0000 19.000 1.2704 0.09409 0.08967 0.0017 0.0190 1.0000 19.250 1.2673 0.09789 0.09355 0.0005 0.0188 1.0000