GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 482 AIRFOIL (goe482-il) Reynolds number: 100,000 Max Cl/Cd: 50.96 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe482-il-100000-n5.txt Download as CSV file: xf-goe482-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 482 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.1831 0.10671 0.10097 -0.1229 0.8362 0.0776
-10.750 0.1720 0.10630 0.10056 -0.1260 0.8280 0.0805
-10.500 0.1693 0.10455 0.09878 -0.1289 0.8215 0.0808
-10.250 0.2010 0.09951 0.09368 -0.1273 0.8153 0.0823
-10.000 0.2180 0.09716 0.09129 -0.1272 0.8083 0.0854
-9.750 0.2268 0.09513 0.08920 -0.1284 0.8021 0.0891
-9.500 0.2115 0.09492 0.08903 -0.1307 0.7934 0.0922
-9.250 0.2078 0.09324 0.08732 -0.1328 0.7868 0.0925
-9.000 0.2326 0.08916 0.08321 -0.1313 0.7806 0.0938
-8.750 0.2526 0.08676 0.08077 -0.1304 0.7737 0.0966
-8.500 0.2633 0.08479 0.07874 -0.1309 0.7680 0.0995
-8.250 0.2651 0.08325 0.07723 -0.1311 0.7596 0.1024
-8.000 0.2468 0.08264 0.07665 -0.1334 0.7520 0.1052
-7.750 0.2388 0.08112 0.07517 -0.1339 0.7439 0.1055
-7.500 0.2542 0.07790 0.07193 -0.1333 0.7373 0.1064
-7.250 0.2829 0.07528 0.06921 -0.1321 0.7321 0.1087
-6.750 0.2544 0.06741 0.06132 -0.1358 0.7172 0.0803
-6.500 0.2636 0.06562 0.05954 -0.1351 0.7099 0.0796
-6.250 0.2685 0.06306 0.05696 -0.1367 0.7026 0.0795
-6.000 0.2773 0.06025 0.05408 -0.1390 0.6967 0.0793
-5.750 0.2845 0.05771 0.05155 -0.1407 0.6884 0.0788
-5.500 0.2982 0.05448 0.04823 -0.1442 0.6826 0.0780
-5.250 0.3114 0.05067 0.04435 -0.1489 0.6753 0.0771
-5.000 0.3354 0.04331 0.03671 -0.1606 0.6689 0.0761
-4.750 0.3727 0.03642 0.02917 -0.1724 0.6643 0.0773
-4.500 0.4018 0.03313 0.02543 -0.1770 0.6564 0.0776
-4.250 0.4346 0.03066 0.02247 -0.1803 0.6504 0.0780
-4.000 0.4662 0.02890 0.02027 -0.1825 0.6447 0.0786
-3.750 0.4947 0.02769 0.01871 -0.1837 0.6376 0.0795
-3.500 0.5262 0.02663 0.01724 -0.1849 0.6323 0.0810
-3.250 0.5530 0.02591 0.01644 -0.1853 0.6261 0.0824
-3.000 0.5800 0.02533 0.01574 -0.1855 0.6196 0.0835
-2.750 0.6100 0.02468 0.01489 -0.1860 0.6147 0.0847
-2.500 0.6364 0.02427 0.01435 -0.1860 0.6086 0.0859
-2.250 0.6634 0.02388 0.01384 -0.1860 0.6025 0.0873
-2.000 0.6929 0.02346 0.01324 -0.1863 0.5977 0.0893
-1.750 0.7192 0.02327 0.01293 -0.1862 0.5920 0.0919
-1.500 0.7452 0.02304 0.01269 -0.1860 0.5862 0.0945
-1.250 0.7738 0.02280 0.01240 -0.1862 0.5814 0.0972
-1.000 0.8010 0.02268 0.01221 -0.1862 0.5764 0.1001
-0.750 0.8259 0.02266 0.01216 -0.1858 0.5706 0.1035
-0.500 0.8538 0.02256 0.01201 -0.1859 0.5657 0.1083
-0.250 0.8841 0.02246 0.01180 -0.1864 0.5617 0.1166
0.000 0.9069 0.02257 0.01201 -0.1858 0.5559 0.1263
0.250 0.9334 0.02257 0.01202 -0.1857 0.5508 0.1435
0.500 0.9626 0.02246 0.01193 -0.1861 0.5466 0.1812
0.750 0.9907 0.02241 0.01210 -0.1865 0.5422 0.2548
1.000 1.0137 0.02266 0.01254 -0.1860 0.5370 0.3359
1.250 1.0395 0.02288 0.01273 -0.1857 0.5323 0.3871
1.500 1.0679 0.02297 0.01283 -0.1859 0.5283 0.4362
1.750 1.0915 0.02318 0.01319 -0.1853 0.5239 0.4862
2.250 1.1371 0.02369 0.01387 -0.1838 0.5146 0.5764
2.500 1.1643 0.02380 0.01397 -0.1837 0.5109 0.6211
2.750 1.1858 0.02392 0.01427 -0.1826 0.5068 0.6924
3.000 1.1967 0.02389 0.01461 -0.1796 0.5019 1.0000
3.250 1.2207 0.02429 0.01488 -0.1792 0.4974 1.0000
3.500 1.2483 0.02459 0.01501 -0.1793 0.4937 1.0000
3.750 1.2736 0.02499 0.01530 -0.1792 0.4900 1.0000
4.000 1.2887 0.02566 0.01599 -0.1775 0.4852 1.0000
4.250 1.3089 0.02616 0.01644 -0.1766 0.4808 1.0000
4.500 1.3340 0.02651 0.01669 -0.1764 0.4771 1.0000
4.750 1.3629 0.02679 0.01681 -0.1767 0.4738 1.0000
5.000 1.3695 0.02765 0.01778 -0.1739 0.4686 1.0000
5.250 1.3835 0.02828 0.01842 -0.1720 0.4642 1.0000
5.500 1.4050 0.02872 0.01880 -0.1713 0.4606 1.0000
5.750 1.4330 0.02902 0.01899 -0.1715 0.4576 1.0000
6.000 1.4396 0.02993 0.01999 -0.1688 0.4535 1.0000
6.250 1.4445 0.03095 0.02108 -0.1659 0.4489 1.0000
6.500 1.4601 0.03161 0.02173 -0.1646 0.4450 1.0000
6.750 1.4845 0.03196 0.02201 -0.1643 0.4418 1.0000
7.000 1.5013 0.03263 0.02268 -0.1631 0.4384 1.0000
7.250 1.4926 0.03439 0.02460 -0.1591 0.4333 1.0000
7.500 1.5016 0.03549 0.02574 -0.1573 0.4294 1.0000
7.750 1.5213 0.03608 0.02631 -0.1566 0.4263 1.0000
8.000 1.5491 0.03630 0.02648 -0.1568 0.4239 1.0000
8.250 1.5341 0.03882 0.02918 -0.1529 0.4191 1.0000
8.500 1.5247 0.04124 0.03173 -0.1499 0.4141 1.0000
8.750 1.5393 0.04218 0.03269 -0.1489 0.4107 1.0000
9.000 1.5665 0.04230 0.03276 -0.1489 0.4082 1.0000
9.250 1.5567 0.04506 0.03566 -0.1463 0.4039 1.0000
9.500 1.5138 0.05083 0.04167 -0.1423 0.3970 1.0000
9.750 1.5284 0.05195 0.04282 -0.1416 0.3941 1.0000
10.000 1.5565 0.05187 0.04272 -0.1416 0.3922 1.0000
10.250 1.5921 0.05118 0.04199 -0.1419 0.3906 1.0000
10.750 1.4984 0.06570 0.05693 -0.1364 0.3757 1.0000
11.000 1.5316 0.06485 0.05608 -0.1363 0.3747 1.0000
11.500 1.4471 0.08163 0.07317 -0.1346 0.3582 1.0000
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Polar data table (+)
Polar graphs
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