XFOIL Version 6.96 Calculated polar for: USA 34 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.2663 0.08909 0.08599 -0.1478 0.8987 0.0230 -16.750 -0.2559 0.08557 0.08222 -0.1520 0.8651 0.0232 -16.500 -0.2533 0.08260 0.07909 -0.1540 0.8413 0.0233 -16.250 -0.2521 0.07961 0.07599 -0.1558 0.8254 0.0235 -16.000 -0.2490 0.07703 0.07331 -0.1574 0.8125 0.0236 -15.750 -0.2530 0.07343 0.06967 -0.1596 0.8022 0.0241 -15.500 -0.2568 0.06993 0.06609 -0.1618 0.7927 0.0242 -15.250 -0.2653 0.06584 0.06195 -0.1644 0.7853 0.0245 -14.750 -0.5307 0.02498 0.02023 -0.2006 0.7668 0.0234 -14.500 -0.5368 0.02308 0.01818 -0.1983 0.7609 0.0235 -14.000 -0.5428 0.02090 0.01579 -0.1907 0.7501 0.0240 -13.750 -0.5360 0.02009 0.01490 -0.1879 0.7455 0.0242 -13.500 -0.5260 0.01941 0.01414 -0.1854 0.7414 0.0245 -13.250 -0.5144 0.01881 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0.01103 0.00392 -0.0814 0.4551 0.1278 1.750 0.6671 0.01119 0.00407 -0.0795 0.4500 0.1330 2.000 0.6869 0.01132 0.00421 -0.0780 0.4469 0.1395 2.250 0.7091 0.01140 0.00432 -0.0769 0.4448 0.1438 2.500 0.7305 0.01152 0.00444 -0.0758 0.4418 0.1474 2.750 0.7514 0.01163 0.00459 -0.0745 0.4381 0.1544 3.000 0.7717 0.01179 0.00475 -0.0732 0.4347 0.1588 3.250 0.7891 0.01203 0.00497 -0.0714 0.4296 0.1629 3.500 0.8104 0.01218 0.00515 -0.0704 0.4261 0.1706 3.750 0.8326 0.01231 0.00532 -0.0695 0.4231 0.1777 4.000 0.8552 0.01245 0.00553 -0.0688 0.4192 0.2032 4.250 0.8764 0.01264 0.00580 -0.0679 0.4152 0.2332 4.500 0.8959 0.01292 0.00611 -0.0668 0.4106 0.2564 4.750 0.9188 0.01311 0.00635 -0.0662 0.4061 0.2724 5.000 0.9410 0.01335 0.00662 -0.0656 0.4010 0.2874 5.250 0.9612 0.01367 0.00696 -0.0647 0.3957 0.3010 5.500 0.9822 0.01399 0.00730 -0.0640 0.3920 0.3142 5.750 1.0067 0.01422 0.00758 -0.0639 0.3879 0.3320 6.250 1.2326 0.01411 0.00892 -0.1021 0.3713 0.9933 6.500 1.2650 0.01456 0.00935 -0.1038 0.3653 0.9974 6.750 1.3124 0.01509 0.00982 -0.1089 0.3584 1.0000 7.000 1.3287 0.01553 0.01026 -0.1073 0.3530 1.0000 7.250 1.3431 0.01607 0.01078 -0.1055 0.3458 1.0000 7.500 1.3563 0.01669 0.01137 -0.1036 0.3393 1.0000 7.750 1.3697 0.01733 0.01197 -0.1018 0.3303 1.0000 8.000 1.3815 0.01806 0.01267 -0.0998 0.3226 1.0000 8.250 1.3916 0.01891 0.01347 -0.0977 0.3107 1.0000 8.500 1.4035 0.01969 0.01422 -0.0958 0.3025 1.0000 8.750 1.4122 0.02067 0.01516 -0.0937 0.2919 1.0000 9.000 1.4236 0.02153 0.01599 -0.0919 0.2827 1.0000 9.250 1.4314 0.02263 0.01704 -0.0898 0.2722 1.0000 9.500 1.4381 0.02381 0.01817 -0.0877 0.2601 1.0000 9.750 1.4427 0.02515 0.01945 -0.0854 0.2456 1.0000 10.000 1.4447 0.02671 0.02093 -0.0829 0.2300 1.0000 10.250 1.4478 0.02823 0.02239 -0.0806 0.2157 1.0000 10.500 1.4469 0.03008 0.02416 -0.0781 0.1999 1.0000 10.750 1.4483 0.03182 0.02586 -0.0759 0.1871 1.0000 11.000 1.4546 0.03327 0.02729 -0.0743 0.1803 1.0000 11.250 1.4624 0.03463 0.02865 -0.0728 0.1750 1.0000 11.500 1.4666 0.03630 0.03030 -0.0711 0.1686 1.0000 11.750 1.4770 0.03750 0.03152 -0.0700 0.1659 1.0000 12.000 1.4850 0.03893 0.03298 -0.0688 0.1632 1.0000 12.250 1.4932 0.04035 0.03441 -0.0676 0.1604 1.0000 12.500 1.5000 0.04192 0.03600 -0.0663 0.1575 1.0000 12.750 1.5064 0.04355 0.03766 -0.0651 0.1546 1.0000 13.000 1.5156 0.04493 0.03907 -0.0642 0.1521 1.0000 13.250 1.5231 0.04652 0.04070 -0.0631 0.1504 1.0000 13.500 1.5303 0.04812 0.04233 -0.0621 0.1482 1.0000 13.750 1.5342 0.05006 0.04428 -0.0610 0.1451 1.0000 14.000 1.5380 0.05205 0.04630 -0.0600 0.1424 1.0000 14.250 1.5438 0.05386 0.04816 -0.0591 0.1406 1.0000 14.500 1.5502 0.05565 0.04999 -0.0583 0.1387 1.0000 14.750 1.5571 0.05738 0.05177 -0.0575 0.1370 1.0000 15.000 1.5602 0.05955 0.05397 -0.0567 0.1343 1.0000 15.250 1.5602 0.06202 0.05646 -0.0558 0.1303 1.0000 15.500 1.5612 0.06445 0.05893 -0.0550 0.1267 1.0000 15.750 1.5634 0.06678 0.06130 -0.0544 0.1232 1.0000 16.000 1.5582 0.06988 0.06439 -0.0535 0.1158 1.0000 16.500 1.5322 0.07803 0.07247 -0.0518 0.0935 1.0000 16.750 1.5262 0.08139 0.07586 -0.0513 0.0893 1.0000 17.000 1.5234 0.08439 0.07889 -0.0509 0.0867 1.0000 17.250 1.5216 0.08732 0.08187 -0.0505 0.0851 1.0000