GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 50,000 Max Cl/Cd: 37.02 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe613-il-50000-n5.txt Download as CSV file: xf-goe613-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3507 0.10192 0.09559 -0.0304 1.0000 0.1267
-7.750 -0.3770 0.10155 0.09539 -0.0291 1.0000 0.1283
-7.500 -0.4019 0.10066 0.09465 -0.0300 1.0000 0.1291
-7.250 -0.3876 0.09595 0.08998 -0.0258 1.0000 0.1319
-7.000 -0.3876 0.09332 0.08741 -0.0236 1.0000 0.1352
-6.750 -0.3957 0.09121 0.08534 -0.0226 1.0000 0.1395
-6.500 -0.4189 0.08996 0.08417 -0.0262 1.0000 0.1444
-6.250 -0.4128 0.08623 0.08051 -0.0221 1.0000 0.1481
-6.000 -0.4140 0.08392 0.07823 -0.0206 1.0000 0.1558
-5.750 -0.4198 0.08112 0.07545 -0.0214 1.0000 0.1628
-5.500 -0.4171 0.07861 0.07297 -0.0193 1.0000 0.1696
-5.000 -0.3618 0.06296 0.05608 -0.0390 0.9917 0.0841
-4.750 -0.3347 0.05882 0.05186 -0.0415 0.9858 0.0828
-4.500 -0.3039 0.05476 0.04739 -0.0453 0.9781 0.0831
-4.250 -0.2741 0.05112 0.04350 -0.0480 0.9708 0.0816
-4.000 -0.2406 0.04760 0.03961 -0.0511 0.9641 0.0796
-3.750 -0.2114 0.04462 0.03619 -0.0529 0.9562 0.0782
-3.500 -0.1764 0.04196 0.03304 -0.0554 0.9502 0.0787
-3.250 -0.1478 0.03994 0.03055 -0.0563 0.9422 0.0809
-3.000 -0.1107 0.03787 0.02796 -0.0585 0.9366 0.0813
-2.750 -0.0832 0.03622 0.02593 -0.0587 0.9280 0.0811
-2.500 -0.0453 0.03460 0.02390 -0.0606 0.9221 0.0812
-2.250 -0.0169 0.03339 0.02237 -0.0608 0.9133 0.0816
-2.000 0.0220 0.03219 0.02082 -0.0626 0.9072 0.0824
-1.750 0.0505 0.03132 0.01971 -0.0627 0.8976 0.0851
-1.500 0.0909 0.03035 0.01868 -0.0651 0.8915 0.0898
-1.250 0.1198 0.02968 0.01787 -0.0650 0.8810 0.0925
-1.000 0.1563 0.02900 0.01699 -0.0662 0.8724 0.0950
-0.750 0.1944 0.02835 0.01616 -0.0676 0.8635 0.0980
-0.500 0.2252 0.02772 0.01550 -0.0679 0.8518 0.1021
-0.250 0.2589 0.02714 0.01484 -0.0686 0.8403 0.1097
0.000 0.2971 0.02642 0.01412 -0.0700 0.8300 0.1273
0.250 0.3337 0.02551 0.01344 -0.0712 0.8188 0.1640
0.500 0.3920 0.02288 0.01302 -0.0763 0.8083 1.0000
0.750 0.4231 0.02275 0.01260 -0.0762 0.7946 1.0000
1.000 0.4541 0.02262 0.01224 -0.0762 0.7808 1.0000
1.250 0.4850 0.02248 0.01190 -0.0761 0.7667 1.0000
1.500 0.5155 0.02234 0.01160 -0.0760 0.7519 1.0000
1.750 0.5456 0.02221 0.01133 -0.0758 0.7365 1.0000
2.000 0.5752 0.02211 0.01111 -0.0755 0.7202 1.0000
2.250 0.6044 0.02204 0.01092 -0.0751 0.7031 1.0000
2.500 0.6334 0.02198 0.01074 -0.0747 0.6853 1.0000
2.750 0.6608 0.02199 0.01066 -0.0741 0.6667 1.0000
3.000 0.6841 0.02213 0.01072 -0.0729 0.6456 1.0000
3.250 0.7107 0.02220 0.01068 -0.0722 0.6257 1.0000
3.500 0.7364 0.02232 0.01071 -0.0714 0.6054 1.0000
3.750 0.7616 0.02251 0.01080 -0.0706 0.5854 1.0000
4.000 0.7884 0.02270 0.01088 -0.0700 0.5664 1.0000
4.250 0.8147 0.02297 0.01101 -0.0694 0.5483 1.0000
4.500 0.8389 0.02337 0.01132 -0.0686 0.5302 1.0000
4.750 0.8631 0.02381 0.01169 -0.0678 0.5132 1.0000
5.000 0.8872 0.02430 0.01215 -0.0671 0.4972 1.0000
5.250 0.9111 0.02484 0.01266 -0.0664 0.4823 1.0000
5.500 0.9349 0.02539 0.01320 -0.0657 0.4681 1.0000
5.750 0.9591 0.02596 0.01379 -0.0652 0.4552 1.0000
6.000 0.9829 0.02655 0.01439 -0.0645 0.4429 1.0000
6.250 1.0043 0.02721 0.01514 -0.0636 0.4310 1.0000
6.500 1.0265 0.02787 0.01588 -0.0628 0.4199 1.0000
6.750 1.0503 0.02851 0.01658 -0.0622 0.4099 1.0000
7.000 1.0721 0.02921 0.01739 -0.0613 0.3999 1.0000
7.250 1.0929 0.02998 0.01829 -0.0604 0.3902 1.0000
7.500 1.1168 0.03063 0.01899 -0.0598 0.3813 1.0000
7.750 1.1354 0.03147 0.02005 -0.0585 0.3717 1.0000
8.000 1.1557 0.03227 0.02098 -0.0575 0.3628 1.0000
8.250 1.1774 0.03300 0.02181 -0.0566 0.3540 1.0000
8.500 1.1932 0.03396 0.02300 -0.0551 0.3449 1.0000
8.750 1.2090 0.03460 0.02378 -0.0533 0.3334 1.0000
9.000 1.2190 0.03512 0.02436 -0.0506 0.3192 1.0000
9.250 1.2262 0.03567 0.02497 -0.0476 0.3048 1.0000
9.500 1.2372 0.03631 0.02570 -0.0452 0.2934 1.0000
9.750 1.2418 0.03728 0.02691 -0.0422 0.2828 1.0000
10.000 1.2430 0.03809 0.02785 -0.0386 0.2709 1.0000
10.250 1.2429 0.03897 0.02882 -0.0351 0.2587 1.0000
10.500 1.2470 0.03996 0.02996 -0.0324 0.2489 1.0000
10.750 1.2487 0.04134 0.03166 -0.0298 0.2397 1.0000
11.000 1.2480 0.04271 0.03318 -0.0272 0.2290 1.0000
11.250 1.2432 0.04438 0.03498 -0.0246 0.2161 1.0000
11.500 1.2391 0.04632 0.03708 -0.0226 0.2033 1.0000
11.750 1.2318 0.04882 0.03978 -0.0210 0.1870 1.0000
12.000 1.2240 0.05170 0.04285 -0.0199 0.1688 1.0000
12.250 1.2138 0.05507 0.04627 -0.0193 0.1460 1.0000
12.500 1.2011 0.05901 0.05013 -0.0191 0.1231 1.0000
12.750 1.1865 0.06361 0.05468 -0.0195 0.1019 1.0000
13.000 1.1697 0.06890 0.05994 -0.0205 0.0813 1.0000
13.250 1.1526 0.07461 0.06564 -0.0221 0.0694 1.0000
13.500 1.1350 0.08073 0.07177 -0.0240 0.0624 1.0000
13.750 1.1201 0.08668 0.07779 -0.0260 0.0585 1.0000
14.000 1.1053 0.09278 0.08395 -0.0282 0.0549 1.0000
14.250 1.0911 0.09892 0.09013 -0.0305 0.0520 1.0000
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Polar data table (+)
Polar graphs
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