GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 200,000 Max Cl/Cd: 74.96 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe517-il-200000.txt Download as CSV file: xf-goe517-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3478 0.08684 0.08349 -0.0254 1.0000 0.0375
-7.250 -0.3530 0.08466 0.08139 -0.0249 1.0000 0.0383
-7.000 -0.3547 0.08220 0.07899 -0.0255 1.0000 0.0393
-6.750 -0.3570 0.07986 0.07671 -0.0269 1.0000 0.0405
-6.500 -0.3607 0.07818 0.07506 -0.0298 1.0000 0.0416
-6.250 -0.3635 0.07640 0.07328 -0.0302 1.0000 0.0419
-6.000 -0.3634 0.07434 0.07117 -0.0309 1.0000 0.0421
-5.750 -0.3548 0.06845 0.06528 -0.0328 0.9978 0.0428
-5.500 -0.3358 0.06449 0.06136 -0.0335 0.9944 0.0442
-5.250 -0.3089 0.06109 0.05792 -0.0367 0.9894 0.0472
-5.000 -0.2436 0.05687 0.05316 -0.0509 0.9835 0.0538
-4.750 -0.2289 0.05058 0.04695 -0.0526 0.9774 0.0553
-4.500 -0.2002 0.04740 0.04375 -0.0551 0.9729 0.0575
-4.250 -0.1652 0.04401 0.04021 -0.0590 0.9682 0.0619
-4.000 -0.1258 0.03922 0.03493 -0.0637 0.9611 0.0680
-3.750 -0.0929 0.03624 0.03194 -0.0664 0.9576 0.0705
-3.500 -0.0579 0.03345 0.02865 -0.0684 0.9503 0.0815
-3.250 -0.0227 0.02543 0.01993 -0.0695 0.9457 0.0511
-3.000 0.0155 0.02054 0.01428 -0.0711 0.9429 0.0470
-2.750 0.0470 0.01869 0.01203 -0.0715 0.9360 0.0500
-2.500 0.0846 0.01713 0.01000 -0.0727 0.9313 0.0535
-2.250 0.1237 0.01547 0.00822 -0.0748 0.9278 0.0592
-2.000 0.1536 0.01482 0.00739 -0.0747 0.9187 0.0674
-1.750 0.1920 0.01403 0.00655 -0.0763 0.9130 0.0797
-1.500 0.2207 0.01332 0.00585 -0.0760 0.9018 0.0962
-1.250 0.2501 0.01282 0.00538 -0.0759 0.8901 0.1151
-1.000 0.2789 0.01241 0.00495 -0.0756 0.8780 0.1327
-0.750 0.3066 0.01206 0.00459 -0.0751 0.8648 0.1502
-0.500 0.3330 0.01171 0.00423 -0.0743 0.8506 0.1666
-0.250 0.3583 0.01134 0.00393 -0.0734 0.8361 0.1861
0.000 0.3831 0.01102 0.00369 -0.0724 0.8217 0.2155
0.250 0.3968 0.00950 0.00354 -0.0696 0.8072 0.6394
0.500 0.4894 0.00885 0.00324 -0.0826 0.7929 1.0000
0.750 0.5130 0.00891 0.00317 -0.0813 0.7752 1.0000
1.000 0.5367 0.00899 0.00311 -0.0802 0.7574 1.0000
1.250 0.5607 0.00907 0.00306 -0.0790 0.7398 1.0000
1.500 0.5843 0.00916 0.00304 -0.0779 0.7208 1.0000
1.750 0.6080 0.00926 0.00304 -0.0768 0.7020 1.0000
2.000 0.6319 0.00937 0.00304 -0.0758 0.6839 1.0000
2.250 0.6558 0.00951 0.00308 -0.0748 0.6664 1.0000
2.500 0.6796 0.00965 0.00314 -0.0737 0.6478 1.0000
2.750 0.7033 0.00982 0.00322 -0.0727 0.6299 1.0000
3.000 0.7270 0.01002 0.00332 -0.0717 0.6127 1.0000
3.250 0.7506 0.01024 0.00346 -0.0707 0.5957 1.0000
3.500 0.7740 0.01047 0.00362 -0.0697 0.5776 1.0000
3.750 0.7973 0.01073 0.00381 -0.0687 0.5593 1.0000
4.000 0.8205 0.01101 0.00403 -0.0677 0.5412 1.0000
4.250 0.8435 0.01133 0.00428 -0.0666 0.5226 1.0000
4.500 0.8662 0.01160 0.00454 -0.0655 0.5015 1.0000
4.750 0.8888 0.01191 0.00480 -0.0644 0.4809 1.0000
5.000 0.9113 0.01219 0.00507 -0.0634 0.4595 1.0000
5.250 0.9335 0.01247 0.00531 -0.0622 0.4377 1.0000
5.500 0.9558 0.01275 0.00559 -0.0611 0.4164 1.0000
5.750 0.9781 0.01307 0.00589 -0.0601 0.3978 1.0000
6.000 0.9998 0.01345 0.00620 -0.0589 0.3793 1.0000
6.250 1.0208 0.01381 0.00653 -0.0577 0.3564 1.0000
6.500 1.0410 0.01426 0.00691 -0.0564 0.3341 1.0000
6.750 1.0619 0.01466 0.00732 -0.0553 0.3130 1.0000
7.000 1.0826 0.01509 0.00775 -0.0541 0.2942 1.0000
7.250 1.1033 0.01546 0.00817 -0.0529 0.2702 1.0000
7.500 1.1222 0.01593 0.00863 -0.0514 0.2358 1.0000
7.750 1.1264 0.01781 0.00966 -0.0482 0.0995 1.0000
8.000 1.1306 0.01997 0.01149 -0.0447 0.0573 1.0000
8.250 1.1409 0.02135 0.01293 -0.0420 0.0483 1.0000
8.500 1.1509 0.02264 0.01426 -0.0394 0.0427 1.0000
8.750 1.1597 0.02402 0.01572 -0.0366 0.0390 1.0000
9.000 1.1709 0.02517 0.01696 -0.0342 0.0362 1.0000
9.250 1.1789 0.02650 0.01835 -0.0314 0.0339 1.0000
9.500 1.1854 0.02828 0.02014 -0.0285 0.0324 1.0000
9.750 1.1983 0.03057 0.02250 -0.0266 0.0308 1.0000
10.000 1.2120 0.03183 0.02392 -0.0247 0.0293 1.0000
10.250 1.2265 0.03344 0.02568 -0.0231 0.0278 1.0000
10.500 1.2426 0.03543 0.02781 -0.0217 0.0267 1.0000
10.750 1.2582 0.03768 0.03024 -0.0204 0.0259 1.0000
11.000 1.2727 0.04022 0.03302 -0.0191 0.0255 1.0000
11.250 1.2836 0.04311 0.03617 -0.0174 0.0253 1.0000
11.500 1.2887 0.04583 0.03913 -0.0153 0.0249 1.0000
11.750 1.2900 0.04865 0.04218 -0.0131 0.0246 1.0000
12.000 1.2889 0.05205 0.04575 -0.0112 0.0239 1.0000
12.250 1.2804 0.05622 0.05017 -0.0091 0.0236 1.0000
12.500 1.2719 0.05875 0.05295 -0.0070 0.0238 1.0000
12.750 1.2584 0.06265 0.05709 -0.0055 0.0237 1.0000
13.000 1.2446 0.06619 0.06086 -0.0046 0.0238 1.0000
13.250 1.2289 0.07005 0.06498 -0.0044 0.0241 1.0000
13.500 1.2011 0.07564 0.07094 -0.0055 0.0250 1.0000
13.750 1.1690 0.08270 0.07832 -0.0084 0.0255 1.0000
14.000 1.1350 0.09131 0.08722 -0.0131 0.0264 1.0000
14.250 1.1075 0.09971 0.09582 -0.0183 0.0268 1.0000
14.500 1.0746 0.11044 0.10673 -0.0252 0.0282 1.0000
14.750 1.0469 0.12120 0.11761 -0.0321 0.0292 1.0000
15.000 1.0230 0.13202 0.12847 -0.0388 0.0301 1.0000
15.250 1.0064 0.14310 0.13964 -0.0451 0.0328 1.0000
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Polar data table (+)
Polar graphs
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