XFOIL Version 6.96 Calculated polar for: ONERA OA213 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.4023 0.09465 0.09051 -0.0142 0.9034 0.0517 -8.250 -0.4062 0.08971 0.08557 -0.0183 0.8974 0.0506 -7.750 -0.4317 0.07152 0.06707 -0.0323 0.8843 0.0278 -7.500 -0.4261 0.06768 0.06313 -0.0339 0.8782 0.0274 -7.250 -0.4222 0.06374 0.05904 -0.0347 0.8724 0.0271 -7.000 -0.4174 0.05967 0.05478 -0.0350 0.8672 0.0267 -6.750 -0.4083 0.05513 0.04997 -0.0359 0.8610 0.0267 -6.500 -0.4003 0.05073 0.04521 -0.0354 0.8557 0.0271 -6.250 -0.3888 0.04606 0.04003 -0.0349 0.8505 0.0276 -6.000 -0.3737 0.04183 0.03524 -0.0343 0.8446 0.0279 -5.750 -0.3577 0.03865 0.03158 -0.0329 0.8397 0.0279 -5.250 -0.3147 0.03353 0.02570 -0.0318 0.8286 0.0285 -5.000 -0.2930 0.03179 0.02370 -0.0307 0.8238 0.0291 -4.750 -0.2686 0.03008 0.02171 -0.0301 0.8187 0.0299 -4.500 -0.2422 0.02860 0.01993 -0.0298 0.8125 0.0318 -4.250 -0.2176 0.02709 0.01802 -0.0286 0.8078 0.0339 -4.000 -0.1920 0.02599 0.01686 -0.0282 0.8026 0.0355 -3.750 -0.1645 0.02485 0.01559 -0.0280 0.7961 0.0373 -3.500 -0.1393 0.02385 0.01438 -0.0268 0.7913 0.0400 -3.250 -0.1136 0.02307 0.01365 -0.0265 0.7856 0.0437 -3.000 -0.0869 0.02227 0.01275 -0.0261 0.7790 0.0476 -2.750 -0.0636 0.02152 0.01205 -0.0249 0.7743 0.0526 -2.500 -0.0370 0.02090 0.01140 -0.0246 0.7673 0.0599 -2.250 -0.0118 0.02032 0.01081 -0.0239 0.7610 0.0703 -2.000 0.0112 0.01968 0.01019 -0.0224 0.7566 0.0857 -1.750 0.0387 0.01913 0.00978 -0.0226 0.7474 0.1169 -1.500 0.0605 0.01817 0.00922 -0.0211 0.7415 0.2085 -1.250 0.0687 0.01608 0.00954 -0.0159 0.7319 0.8056 -1.000 0.0917 0.01604 0.00946 -0.0120 0.7248 0.9007 -0.750 0.1411 0.01616 0.00939 -0.0142 0.7129 0.9542 -0.500 0.2461 0.01599 0.00888 -0.0277 0.7009 0.9983 -0.250 0.2714 0.01575 0.00845 -0.0271 0.6919 1.0000 0.000 0.2959 0.01562 0.00819 -0.0267 0.6799 1.0000 0.250 0.3200 0.01550 0.00794 -0.0261 0.6682 1.0000 0.500 0.3432 0.01536 0.00767 -0.0252 0.6567 1.0000 0.750 0.3659 0.01521 0.00738 -0.0242 0.6451 1.0000 1.000 0.3902 0.01515 0.00721 -0.0236 0.6310 1.0000 1.250 0.4141 0.01510 0.00704 -0.0230 0.6164 1.0000 1.500 0.4378 0.01506 0.00688 -0.0222 0.6009 1.0000 1.750 0.4614 0.01504 0.00675 -0.0215 0.5847 1.0000 2.000 0.4850 0.01505 0.00662 -0.0207 0.5672 1.0000 2.250 0.5086 0.01510 0.00654 -0.0200 0.5480 1.0000 2.500 0.5326 0.01521 0.00652 -0.0195 0.5268 1.0000 2.750 0.5561 0.01534 0.00650 -0.0188 0.5043 1.0000 3.000 0.5798 0.01552 0.00653 -0.0183 0.4795 1.0000 3.250 0.6032 0.01576 0.00660 -0.0177 0.4540 1.0000 3.500 0.6266 0.01605 0.00672 -0.0172 0.4272 1.0000 3.750 0.6498 0.01641 0.00688 -0.0167 0.4018 1.0000 4.000 0.6730 0.01681 0.00710 -0.0163 0.3782 1.0000 4.250 0.6961 0.01725 0.00737 -0.0159 0.3580 1.0000 4.500 0.7194 0.01770 0.00768 -0.0156 0.3400 1.0000 4.750 0.7428 0.01817 0.00802 -0.0153 0.3243 1.0000 5.250 0.7899 0.01912 0.00880 -0.0148 0.2988 1.0000 5.500 0.8135 0.01961 0.00921 -0.0145 0.2883 1.0000 6.000 0.8605 0.02062 0.01013 -0.0140 0.2697 1.0000 6.250 0.8835 0.02117 0.01059 -0.0138 0.2622 1.0000 6.500 0.9073 0.02167 0.01111 -0.0136 0.2546 1.0000 6.750 0.9301 0.02225 0.01163 -0.0133 0.2484 1.0000 7.000 0.9536 0.02279 0.01221 -0.0130 0.2420 1.0000 7.250 0.9765 0.02336 0.01277 -0.0128 0.2359 1.0000 7.500 0.9991 0.02398 0.01334 -0.0125 0.2308 1.0000 7.750 1.0221 0.02456 0.01402 -0.0123 0.2252 1.0000 8.000 1.0446 0.02519 0.01466 -0.0120 0.2206 1.0000 8.250 1.0671 0.02587 0.01528 -0.0117 0.2169 1.0000 8.500 1.0897 0.02653 0.01609 -0.0114 0.2127 1.0000 8.750 1.1117 0.02722 0.01686 -0.0111 0.2086 1.0000 9.000 1.1335 0.02792 0.01759 -0.0108 0.2049 1.0000 9.250 1.1556 0.02866 0.01830 -0.0106 0.2018 1.0000 9.500 1.1763 0.02946 0.01927 -0.0102 0.1982 1.0000 9.750 1.1968 0.03027 0.02021 -0.0098 0.1948 1.0000 10.000 1.2175 0.03109 0.02113 -0.0095 0.1919 1.0000 10.250 1.2385 0.03191 0.02201 -0.0092 0.1895 1.0000 10.500 1.2605 0.03277 0.02288 -0.0089 0.1873 1.0000 10.750 1.2797 0.03379 0.02408 -0.0085 0.1851 1.0000 11.000 1.2971 0.03489 0.02540 -0.0080 0.1828 1.0000 11.250 1.3141 0.03600 0.02670 -0.0075 0.1805 1.0000 11.500 1.3296 0.03705 0.02789 -0.0069 0.1779 1.0000 11.750 1.3438 0.03790 0.02880 -0.0060 0.1750 1.0000 12.000 1.3583 0.03877 0.02968 -0.0053 0.1718 1.0000 12.250 1.3594 0.04030 0.03152 -0.0038 0.1684 1.0000 12.500 1.3639 0.04168 0.03309 -0.0028 0.1648 1.0000 12.750 1.3719 0.04282 0.03430 -0.0020 0.1613 1.0000 13.000 1.3841 0.04376 0.03523 -0.0014 0.1584 1.0000 13.250 1.3825 0.04593 0.03771 -0.0006 0.1557 1.0000 13.500 1.3823 0.04810 0.04014 0.0000 0.1529 1.0000 13.750 1.3842 0.05015 0.04238 0.0003 0.1502 1.0000 14.000 1.3880 0.05199 0.04435 0.0006 0.1476 1.0000 14.250 1.3955 0.05341 0.04578 0.0008 0.1448 1.0000 14.500 1.3855 0.05698 0.04966 0.0006 0.1423 1.0000 14.750 1.3749 0.06080 0.05376 0.0000 0.1398 1.0000 15.000 1.3655 0.06465 0.05782 -0.0009 0.1373 1.0000 15.250 1.3587 0.06827 0.06161 -0.0019 0.1348 1.0000 15.500 1.3593 0.07097 0.06440 -0.0027 0.1322 1.0000 15.750 1.3415 0.07668 0.07033 -0.0048 0.1304 1.0000 16.000 1.3088 0.08515 0.07907 -0.0084 0.1294 1.0000 16.250 1.2559 0.09772 0.09188 -0.0141 0.1297 1.0000