XFOIL Version 6.96 Calculated polar for: FX 71-L-150/30 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -0.9798 0.14046 0.13812 0.0119 1.0000 0.0144 -19.000 -1.0622 0.11821 0.11539 -0.0019 1.0000 0.0139 -18.750 -1.0894 0.10883 0.10580 -0.0073 1.0000 0.0137 -18.500 -1.1066 0.10180 0.09861 -0.0111 1.0000 0.0136 -18.250 -1.1247 0.09475 0.09137 -0.0148 1.0000 0.0134 -18.000 -1.1346 0.08936 0.08585 -0.0176 1.0000 0.0134 -17.750 -1.1457 0.08389 0.08024 -0.0203 1.0000 0.0133 -17.500 -1.1535 0.07914 0.07536 -0.0224 1.0000 0.0132 -17.250 -1.1576 0.07501 0.07112 -0.0243 1.0000 0.0132 -17.000 -1.1621 0.07105 0.06706 -0.0258 1.0000 0.0132 -16.750 -1.1649 0.06736 0.06326 -0.0272 1.0000 0.0131 -16.500 -1.1666 0.06395 0.05976 -0.0284 1.0000 0.0131 -16.250 -1.1674 0.06073 0.05645 -0.0293 1.0000 0.0131 -16.000 -1.1664 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0.4011 0.6648 3.500 0.3955 0.00768 0.00208 0.0001 0.3372 0.6689 3.750 0.4203 0.00814 0.00233 0.0005 0.2786 0.6727 4.000 0.4447 0.00866 0.00260 0.0009 0.2189 0.6762 4.250 0.4689 0.00920 0.00288 0.0013 0.1634 0.6795 4.500 0.4930 0.00970 0.00318 0.0018 0.1179 0.6827 4.750 0.5175 0.01016 0.00348 0.0023 0.0836 0.6857 5.000 0.5426 0.01056 0.00376 0.0026 0.0581 0.6889 5.250 0.5684 0.01089 0.00401 0.0029 0.0433 0.6922 5.500 0.5935 0.01125 0.00430 0.0033 0.0301 0.6950 5.750 0.6194 0.01152 0.00456 0.0036 0.0250 0.6976 6.000 0.6453 0.01180 0.00481 0.0039 0.0198 0.7006 6.250 0.6710 0.01208 0.00507 0.0042 0.0177 0.7037 6.500 0.6968 0.01236 0.00534 0.0046 0.0169 0.7065 6.750 0.7219 0.01263 0.00562 0.0050 0.0163 0.7092 7.000 0.7467 0.01293 0.00594 0.0054 0.0158 0.7120 7.250 0.7712 0.01324 0.00627 0.0059 0.0155 0.7150 7.500 0.7955 0.01357 0.00662 0.0064 0.0153 0.7181 7.750 0.8193 0.01389 0.00697 0.0070 0.0151 0.7211 8.000 0.8424 0.01422 0.00735 0.0077 0.0148 0.7242 8.250 0.8647 0.01460 0.00777 0.0085 0.0145 0.7272 8.500 0.8865 0.01501 0.00822 0.0093 0.0143 0.7300 8.750 0.9076 0.01546 0.00869 0.0103 0.0142 0.7324 9.000 0.9272 0.01592 0.00919 0.0114 0.0139 0.7353 9.250 0.9465 0.01636 0.00969 0.0125 0.0139 0.7380 9.500 0.9634 0.01692 0.01030 0.0140 0.0137 0.7408 9.750 0.9792 0.01748 0.01091 0.0156 0.0136 0.7436 10.000 0.9902 0.01809 0.01156 0.0180 0.0135 0.7465 10.250 0.9953 0.01881 0.01235 0.0212 0.0133 0.7500 10.500 1.0023 0.01956 0.01317 0.0238 0.0133 0.7537 10.750 1.0123 0.02027 0.01394 0.0258 0.0133 0.7576 11.000 1.0153 0.02146 0.01520 0.0281 0.0132 0.7618 11.250 1.0221 0.02255 0.01637 0.0298 0.0132 0.7669 11.500 1.0285 0.02379 0.01767 0.0312 0.0131 0.7726 11.750 1.0316 0.02528 0.01926 0.0329 0.0131 0.7793 12.000 1.0443 0.02611 0.02017 0.0338 0.0132 0.7881 12.250 1.0437 0.02777 0.02200 0.0357 0.0130 0.8097 12.500 1.0844 0.02919 0.02390 0.0300 0.0131 0.9539 12.750 1.1024 0.03098 0.02575 0.0284 0.0130 1.0000 13.000 1.1118 0.03246 0.02727 0.0289 0.0131 1.0000 13.250 1.1192 0.03414 0.02900 0.0294 0.0131 1.0000 13.500 1.1289 0.03562 0.03053 0.0297 0.0131 1.0000 13.750 1.1359 0.03738 0.03235 0.0301 0.0131 1.0000 14.000 1.1432 0.03912 0.03415 0.0303 0.0131 1.0000 14.250 1.1499 0.04095 0.03604 0.0305 0.0131 1.0000 14.500 1.1548 0.04299 0.03814 0.0307 0.0131 1.0000 14.750 1.1575 0.04524 0.04047 0.0311 0.0131 1.0000 15.000 1.1585 0.04772 0.04303 0.0313 0.0130 1.0000 15.250 1.1630 0.04991 0.04529 0.0311 0.0130 1.0000 15.500 1.1648 0.05245 0.04792 0.0309 0.0130 1.0000 15.750 1.1672 0.05504 0.05059 0.0304 0.0131 1.0000 16.000 1.1693 0.05775 0.05337 0.0298 0.0131 1.0000 16.250 1.1697 0.06072 0.05644 0.0290 0.0131 1.0000 16.500 1.1687 0.06397 0.05979 0.0280 0.0131 1.0000 16.750 1.1673 0.06737 0.06328 0.0268 0.0132 1.0000 17.000 1.1658 0.07088 0.06688 0.0255 0.0132 1.0000 17.250 1.1611 0.07491 0.07102 0.0239 0.0132 1.0000 17.500 1.1542 0.07939 0.07562 0.0220 0.0133 1.0000 17.750 1.1485 0.08385 0.08019 0.0199 0.0133 1.0000 18.000 1.1369 0.08938 0.08587 0.0172 0.0134 1.0000 18.250 1.1260 0.09498 0.09161 0.0143 0.0135 1.0000 18.500 1.1157 0.10060 0.09734 0.0114 0.0134 1.0000