XFOIL Version 6.96 Calculated polar for: GOE 622 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.5432 0.12888 0.12723 0.0048 1.0000 0.0028 -11.250 -0.5411 0.12445 0.12280 0.0032 1.0000 0.0029 -10.250 -0.8227 0.02976 0.02725 -0.0542 1.0000 0.0025 -10.000 -0.8112 0.02654 0.02373 -0.0539 1.0000 0.0026 -9.750 -0.7960 0.02430 0.02125 -0.0533 1.0000 0.0026 -9.500 -0.7784 0.02264 0.01940 -0.0525 1.0000 0.0027 -9.250 -0.7596 0.02123 0.01782 -0.0518 1.0000 0.0028 -9.000 -0.7398 0.02007 0.01651 -0.0509 1.0000 0.0029 -8.750 -0.7196 0.01899 0.01527 -0.0501 1.0000 0.0030 -8.500 -0.6966 0.01784 0.01395 -0.0497 0.9995 0.0032 -8.250 -0.6662 0.01664 0.01252 -0.0510 0.9975 0.0033 -8.000 -0.6344 0.01549 0.01118 -0.0524 0.9953 0.0035 -7.750 -0.6035 0.01452 0.01003 -0.0535 0.9918 0.0036 -7.500 -0.5718 0.01374 0.00911 -0.0547 0.9882 0.0038 -7.250 -0.5419 0.01277 0.00798 -0.0555 0.9829 0.0040 -6.750 -0.4798 0.01143 0.00645 -0.0574 0.9678 0.0045 -6.500 -0.4481 0.01095 0.00589 -0.0583 0.9560 0.0049 -6.250 -0.4178 0.01050 0.00534 -0.0589 0.9418 0.0052 -6.000 -0.3898 0.01012 0.00483 -0.0590 0.9283 0.0056 -5.750 -0.3625 0.00985 0.00448 -0.0588 0.9170 0.0059 -5.500 -0.3359 0.00940 0.00393 -0.0586 0.9066 0.0069 -5.000 -0.2818 0.00886 0.00325 -0.0582 0.8888 0.0085 -4.750 -0.2545 0.00866 0.00297 -0.0580 0.8813 0.0092 -4.500 -0.2271 0.00836 0.00262 -0.0579 0.8732 0.0120 -4.250 -0.1998 0.00815 0.00238 -0.0578 0.8655 0.0159 -4.000 -0.1723 0.00794 0.00217 -0.0577 0.8575 0.0241 -3.750 -0.1447 0.00776 0.00199 -0.0576 0.8503 0.0301 -3.500 -0.1170 0.00763 0.00182 -0.0575 0.8422 0.0352 -3.250 -0.0893 0.00747 0.00166 -0.0575 0.8337 0.0427 -3.000 -0.0616 0.00733 0.00151 -0.0574 0.8247 0.0525 -2.750 -0.0340 0.00718 0.00139 -0.0574 0.8151 0.0689 -2.500 -0.0064 0.00708 0.00129 -0.0573 0.8015 0.0860 -2.250 0.0211 0.00702 0.00120 -0.0571 0.7848 0.0954 -2.000 0.0486 0.00701 0.00110 -0.0570 0.7636 0.1003 -1.750 0.0762 0.00697 0.00102 -0.0569 0.7448 0.1072 -1.500 0.1034 0.00700 0.00095 -0.0567 0.7169 0.1131 -1.250 0.1301 0.00706 0.00088 -0.0564 0.6770 0.1228 -1.000 0.1564 0.00719 0.00085 -0.0562 0.6290 0.1349 -0.750 0.1831 0.00721 0.00083 -0.0560 0.5914 0.1688 -0.500 0.2101 0.00713 0.00081 -0.0560 0.5676 0.2222 -0.250 0.2375 0.00702 0.00080 -0.0560 0.5501 0.2807 0.000 0.2650 0.00690 0.00081 -0.0560 0.5360 0.3425 0.250 0.2924 0.00678 0.00082 -0.0561 0.5232 0.4052 0.500 0.3199 0.00664 0.00083 -0.0561 0.5116 0.4764 0.750 0.3471 0.00648 0.00086 -0.0561 0.4993 0.5576 1.000 0.3741 0.00631 0.00090 -0.0560 0.4858 0.6436 1.250 0.4001 0.00609 0.00096 -0.0557 0.4708 0.7505 1.500 0.4233 0.00587 0.00104 -0.0546 0.4526 0.8680 1.750 0.4469 0.00587 0.00112 -0.0533 0.4196 0.9533 2.000 0.4854 0.00625 0.00122 -0.0560 0.3494 1.0000 2.250 0.5113 0.00654 0.00134 -0.0557 0.3109 1.0000 2.500 0.5374 0.00680 0.00146 -0.0554 0.2800 1.0000 2.750 0.5635 0.00709 0.00160 -0.0552 0.2451 1.0000 3.000 0.5898 0.00733 0.00173 -0.0550 0.2199 1.0000 3.250 0.6165 0.00754 0.00187 -0.0548 0.2014 1.0000 3.500 0.6414 0.00801 0.00208 -0.0545 0.1456 1.0000 3.750 0.6674 0.00833 0.00228 -0.0542 0.1209 1.0000 4.000 0.6940 0.00855 0.00246 -0.0541 0.1094 1.0000 4.250 0.7204 0.00879 0.00265 -0.0539 0.0980 1.0000 4.500 0.7462 0.00913 0.00285 -0.0536 0.0699 1.0000 4.750 0.7716 0.00953 0.00314 -0.0533 0.0458 1.0000 5.000 0.7962 0.01005 0.00350 -0.0529 0.0185 1.0000 5.250 0.8225 0.01031 0.00377 -0.0526 0.0123 1.0000 5.500 0.8488 0.01056 0.00405 -0.0524 0.0105 1.0000 5.750 0.8747 0.01088 0.00440 -0.0521 0.0087 1.0000 6.000 0.9001 0.01127 0.00483 -0.0517 0.0072 1.0000 6.250 0.9259 0.01157 0.00518 -0.0514 0.0067 1.0000 6.500 0.9514 0.01191 0.00555 -0.0511 0.0060 1.0000 6.750 0.9765 0.01228 0.00594 -0.0508 0.0054 1.0000 7.000 1.0007 0.01281 0.00650 -0.0502 0.0047 1.0000 7.250 1.0256 0.01320 0.00695 -0.0498 0.0044 1.0000 7.500 1.0501 0.01365 0.00745 -0.0494 0.0041 1.0000 7.750 1.0741 0.01414 0.00799 -0.0488 0.0039 1.0000 8.000 1.0979 0.01465 0.00857 -0.0483 0.0036 1.0000 8.250 1.1214 0.01517 0.00915 -0.0477 0.0034 1.0000 8.500 1.1441 0.01579 0.00982 -0.0471 0.0032 1.0000 8.750 1.1637 0.01682 0.01095 -0.0459 0.0030 1.0000 9.000 1.1858 0.01745 0.01165 -0.0452 0.0029 1.0000 9.250 1.2076 0.01809 0.01238 -0.0444 0.0027 1.0000 9.500 1.2287 0.01879 0.01316 -0.0436 0.0026 1.0000 9.750 1.2489 0.01956 0.01402 -0.0426 0.0024 1.0000 10.000 1.2680 0.02043 0.01498 -0.0415 0.0023 1.0000 10.250 1.2863 0.02134 0.01599 -0.0403 0.0022 1.0000 10.500 1.3040 0.02227 0.01702 -0.0391 0.0022 1.0000 10.750 1.3208 0.02322 0.01810 -0.0378 0.0021 1.0000 11.000 1.3368 0.02419 0.01917 -0.0364 0.0020 1.0000 11.250 1.3512 0.02524 0.02032 -0.0349 0.0020 1.0000 11.500 1.3642 0.02634 0.02153 -0.0332 0.0019 1.0000 11.750 1.3726 0.02756 0.02287 -0.0308 0.0019 1.0000 12.000 1.3765 0.02900 0.02443 -0.0280 0.0018 1.0000 12.250 1.3767 0.03080 0.02639 -0.0251 0.0018 1.0000 12.500 1.3709 0.03325 0.02903 -0.0223 0.0017 1.0000 12.750 1.3630 0.03613 0.03211 -0.0201 0.0017 1.0000 13.000 1.3616 0.03859 0.03473 -0.0189 0.0017 1.0000 13.250 1.3570 0.04161 0.03791 -0.0182 0.0017 1.0000 13.500 1.3505 0.04512 0.04159 -0.0181 0.0017 1.0000 13.750 1.3432 0.04908 0.04573 -0.0187 0.0016 1.0000 14.000 1.3322 0.05391 0.05074 -0.0202 0.0016 1.0000 14.250 1.3192 0.05951 0.05651 -0.0225 0.0016 1.0000 14.500 1.3056 0.06553 0.06268 -0.0254 0.0016 1.0000 14.750 1.2869 0.07275 0.07007 -0.0291 0.0016 1.0000 15.000 1.2665 0.08061 0.07809 -0.0332 0.0016 1.0000 15.250 1.2426 0.08962 0.08725 -0.0380 0.0016 1.0000 15.500 1.2164 0.09960 0.09737 -0.0433 0.0017 1.0000 15.750 1.1919 0.10950 0.10740 -0.0484 0.0017 1.0000 16.000 1.1686 0.11934 0.11735 -0.0533 0.0017 1.0000 16.250 1.1401 0.13054 0.12865 -0.0589 0.0017 1.0000 16.500 1.1162 0.14117 0.13938 -0.0642 0.0017 1.0000