XFOIL Version 6.96 Calculated polar for: WORTMANN FX 71-089A AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.9332 0.06903 0.06601 -0.0288 1.0000 0.0425 -12.750 -0.9764 0.05920 0.05601 -0.0362 1.0000 0.0422 -12.500 -1.0141 0.05298 0.04957 -0.0389 1.0000 0.0421 -12.250 -1.0448 0.04893 0.04530 -0.0375 1.0000 0.0422 -12.000 -1.0684 0.04615 0.04227 -0.0337 1.0000 0.0423 -11.750 -1.0778 0.04405 0.03988 -0.0309 1.0000 0.0426 -11.500 -1.0924 0.03929 0.03476 -0.0283 1.0000 0.0431 -11.250 -1.0828 0.03703 0.03243 -0.0271 1.0000 0.0437 -11.000 -1.0636 0.03633 0.03177 -0.0263 1.0000 0.0443 -10.750 -1.0419 0.03606 0.03155 -0.0256 1.0000 0.0449 -10.500 -1.0243 0.03529 0.03074 -0.0245 1.0000 0.0456 -10.250 -1.0106 0.03391 0.02921 -0.0231 1.0000 0.0465 -10.000 -0.9982 0.03219 0.02726 -0.0215 1.0000 0.0472 -9.750 -0.9845 0.03050 0.02532 -0.0199 1.0000 0.0478 -9.500 -0.9686 0.02914 0.02372 -0.0184 1.0000 0.0483 -9.250 -0.9511 0.02795 0.02232 -0.0169 1.0000 0.0487 -9.000 -0.9329 0.02664 0.02083 -0.0156 1.0000 0.0488 -8.750 -0.9145 0.02530 0.01928 -0.0142 1.0000 0.0491 -8.500 -0.8956 0.02349 0.01730 -0.0130 1.0000 0.0492 -8.250 -0.8753 0.02196 0.01564 -0.0119 1.0000 0.0494 -8.000 -0.8540 0.02066 0.01424 -0.0109 1.0000 0.0496 -7.750 -0.8323 0.01950 0.01301 -0.0098 1.0000 0.0498 -7.500 -0.8101 0.01853 0.01198 -0.0088 1.0000 0.0501 -7.250 -0.7877 0.01769 0.01110 -0.0078 1.0000 0.0504 -7.000 -0.7651 0.01696 0.01035 -0.0067 1.0000 0.0507 -6.750 -0.7425 0.01630 0.00966 -0.0056 1.0000 0.0511 -6.500 -0.7198 0.01569 0.00903 -0.0045 1.0000 0.0515 -6.250 -0.6972 0.01513 0.00845 -0.0034 1.0000 0.0519 -6.000 -0.6746 0.01462 0.00793 -0.0023 1.0000 0.0524 -5.750 -0.6520 0.01416 0.00746 -0.0011 1.0000 0.0531 -5.500 -0.6296 0.01370 0.00698 0.0001 1.0000 0.0536 -5.250 -0.6073 0.01325 0.00651 0.0013 1.0000 0.0541 -5.000 -0.5852 0.01283 0.00608 0.0026 1.0000 0.0546 -4.750 -0.5632 0.01243 0.00568 0.0039 1.0000 0.0551 -4.500 -0.5412 0.01209 0.00532 0.0052 1.0000 0.0556 -4.250 -0.5193 0.01178 0.00501 0.0066 1.0000 0.0561 -4.000 -0.4989 0.01128 0.00451 0.0081 1.0000 0.0570 -3.750 -0.4780 0.01090 0.00417 0.0096 1.0000 0.0581 -3.500 -0.4566 0.01064 0.00393 0.0110 1.0000 0.0592 -3.250 -0.4352 0.01042 0.00373 0.0123 1.0000 0.0605 -3.000 -0.4136 0.01025 0.00357 0.0136 1.0000 0.0622 -2.750 -0.3731 0.01006 0.00340 0.0111 0.9964 0.0642 -2.500 -0.3326 0.00971 0.00312 0.0085 0.9922 0.0684 -2.250 -0.2913 0.00943 0.00289 0.0059 0.9865 0.0748 -2.000 -0.2498 0.00894 0.00266 0.0030 0.9818 0.1113 -1.750 -0.2121 0.00837 0.00245 0.0010 0.9734 0.1818 -1.500 -0.1716 0.00780 0.00224 -0.0016 0.9624 0.2658 -1.250 -0.1339 0.00722 0.00206 -0.0035 0.9471 0.3604 -1.000 -0.0996 0.00669 0.00193 -0.0047 0.9287 0.4654 -0.750 -0.0692 0.00625 0.00181 -0.0048 0.8945 0.5654 -0.500 -0.0447 0.00599 0.00173 -0.0036 0.8546 0.6444 -0.250 -0.0222 0.00585 0.00171 -0.0018 0.8109 0.7090 0.000 0.0000 0.00583 0.00169 0.0000 0.7621 0.7619 0.250 0.0222 0.00585 0.00171 0.0018 0.7093 0.8108 0.500 0.0447 0.00599 0.00173 0.0035 0.6449 0.8539 0.750 0.0691 0.00625 0.00181 0.0048 0.5651 0.8943 1.000 0.0995 0.00669 0.00193 0.0047 0.4659 0.9285 1.250 0.1341 0.00723 0.00207 0.0035 0.3604 0.9474 1.500 0.1715 0.00781 0.00224 0.0016 0.2641 0.9624 1.750 0.2125 0.00838 0.00245 -0.0011 0.1819 0.9735 2.000 0.2500 0.00892 0.00266 -0.0031 0.1145 0.9818 2.250 0.2912 0.00943 0.00289 -0.0059 0.0748 0.9865 2.500 0.3323 0.00971 0.00312 -0.0084 0.0684 0.9921 2.750 0.3733 0.01006 0.00340 -0.0111 0.0642 0.9964 3.000 0.4135 0.01024 0.00357 -0.0136 0.0621 1.0000 3.250 0.4351 0.01042 0.00373 -0.0123 0.0604 1.0000 3.500 0.4565 0.01064 0.00393 -0.0109 0.0592 1.0000 3.750 0.4779 0.01091 0.00417 -0.0096 0.0580 1.0000 4.000 0.4988 0.01128 0.00452 -0.0081 0.0569 1.0000 4.250 0.5192 0.01178 0.00500 -0.0066 0.0560 1.0000 4.500 0.5412 0.01208 0.00532 -0.0052 0.0556 1.0000 4.750 0.5631 0.01243 0.00567 -0.0039 0.0551 1.0000 5.000 0.5851 0.01282 0.00607 -0.0026 0.0546 1.0000 5.250 0.6073 0.01324 0.00651 -0.0013 0.0541 1.0000 5.500 0.6295 0.01370 0.00698 -0.0001 0.0536 1.0000 5.750 0.6519 0.01417 0.00746 0.0011 0.0531 1.0000 6.000 0.6745 0.01463 0.00793 0.0023 0.0524 1.0000 6.250 0.6972 0.01512 0.00844 0.0034 0.0519 1.0000 6.500 0.7198 0.01569 0.00903 0.0046 0.0515 1.0000 6.750 0.7424 0.01630 0.00965 0.0056 0.0511 1.0000 7.000 0.7651 0.01696 0.01035 0.0067 0.0507 1.0000 7.250 0.7876 0.01770 0.01111 0.0078 0.0504 1.0000 7.500 0.8101 0.01853 0.01198 0.0088 0.0501 1.0000 7.750 0.8322 0.01952 0.01302 0.0098 0.0498 1.0000 8.000 0.8540 0.02067 0.01424 0.0109 0.0496 1.0000 8.250 0.8752 0.02199 0.01567 0.0119 0.0494 1.0000 8.500 0.8956 0.02348 0.01729 0.0130 0.0492 1.0000 8.750 0.9146 0.02529 0.01927 0.0142 0.0491 1.0000 9.000 0.9330 0.02655 0.02073 0.0156 0.0488 1.0000 9.250 0.9513 0.02787 0.02224 0.0169 0.0487 1.0000 9.500 0.9689 0.02900 0.02358 0.0183 0.0482 1.0000 9.750 0.9849 0.03038 0.02519 0.0199 0.0477 1.0000 10.000 0.9985 0.03213 0.02720 0.0215 0.0471 1.0000 10.250 1.0111 0.03385 0.02914 0.0231 0.0464 1.0000 10.500 1.0256 0.03511 0.03053 0.0244 0.0456 1.0000 10.750 1.0432 0.03591 0.03138 0.0255 0.0448 1.0000 11.000 1.0629 0.03646 0.03191 0.0263 0.0443 1.0000 11.250 1.0828 0.03707 0.03247 0.0271 0.0437 1.0000 11.500 1.0930 0.03921 0.03468 0.0283 0.0431 1.0000 12.000 1.0683 0.04597 0.04211 0.0337 0.0422 1.0000 12.250 1.0447 0.04896 0.04533 0.0374 0.0421 1.0000 12.500 1.0141 0.05297 0.04956 0.0388 0.0420 1.0000 12.750 0.9784 0.05917 0.05597 0.0362 0.0422 1.0000 13.000 0.9414 0.06796 0.06490 0.0303 0.0426 1.0000