GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 200,000 Max Cl/Cd: 81.05 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe431-il-200000.txt Download as CSV file: xf-goe431-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1025 0.10838 0.10479 -0.0903 0.9588 0.0631
-9.750 -0.1128 0.10602 0.10246 -0.0954 0.9515 0.0649
-9.500 -0.1015 0.10143 0.09788 -0.0970 0.9489 0.0663
-9.250 -0.0769 0.09866 0.09508 -0.0970 0.9475 0.0681
-9.000 -0.0589 0.09571 0.09212 -0.0995 0.9458 0.0707
-8.750 0.0231 0.07735 0.07393 -0.1082 0.9306 0.0789
-8.500 0.0451 0.07459 0.07114 -0.1095 0.9297 0.0829
-8.250 -0.0856 0.07525 0.07172 -0.1127 0.9306 0.0461
-8.000 -0.2310 0.04448 0.04048 -0.1426 0.9049 0.0361
-7.750 -0.1907 0.03570 0.03086 -0.1608 0.9025 0.0361
-7.500 -0.1556 0.03150 0.02610 -0.1675 0.9013 0.0368
-7.250 -0.1234 0.02902 0.02345 -0.1706 0.9004 0.0382
-7.000 -0.0890 0.02764 0.02191 -0.1733 0.8995 0.0407
-6.750 -0.0857 0.02742 0.02157 -0.1699 0.8945 0.0423
-6.500 -0.0664 0.02685 0.02076 -0.1693 0.8918 0.0442
-6.250 -0.0406 0.02544 0.01934 -0.1701 0.8901 0.0471
-6.000 -0.0120 0.02469 0.01852 -0.1710 0.8887 0.0511
-5.750 0.0241 0.02353 0.01726 -0.1733 0.8871 0.0590
-5.500 0.0711 0.02182 0.01540 -0.1776 0.8857 0.0788
-5.250 0.1227 0.02230 0.01608 -0.1812 0.8842 0.1424
-5.000 0.1154 0.02356 0.01729 -0.1751 0.8770 0.1506
-4.750 0.1482 0.02434 0.01812 -0.1753 0.8731 0.1647
-4.500 0.1906 0.02482 0.01870 -0.1771 0.8709 0.1780
-4.250 0.2405 0.02459 0.01840 -0.1806 0.8698 0.1896
-4.000 0.2416 0.02536 0.01921 -0.1759 0.8626 0.1934
-3.750 0.2750 0.02511 0.01867 -0.1769 0.8590 0.2003
-3.500 0.3175 0.02451 0.01817 -0.1793 0.8572 0.2066
-3.250 0.3675 0.02394 0.01741 -0.1830 0.8561 0.2152
-3.000 0.4138 0.02293 0.01630 -0.1863 0.8549 0.2203
-2.750 0.4589 0.02198 0.01524 -0.1892 0.8536 0.2222
-2.500 0.4569 0.02256 0.01577 -0.1842 0.8456 0.2225
-2.250 0.4944 0.02185 0.01491 -0.1859 0.8431 0.2233
-2.000 0.5357 0.02107 0.01402 -0.1882 0.8413 0.2250
-1.750 0.5781 0.02028 0.01310 -0.1905 0.8395 0.2268
-1.500 0.6214 0.01946 0.01215 -0.1930 0.8378 0.2280
-1.250 0.6316 0.01971 0.01238 -0.1898 0.8300 0.2287
-1.000 0.6700 0.01903 0.01160 -0.1913 0.8265 0.2302
-0.750 0.7121 0.01828 0.01075 -0.1934 0.8238 0.2319
-0.500 0.7416 0.01791 0.01035 -0.1934 0.8188 0.2336
-0.250 0.7666 0.01763 0.01010 -0.1926 0.8125 0.2356
0.000 0.8055 0.01697 0.00944 -0.1941 0.8086 0.2386
0.250 0.8334 0.01667 0.00917 -0.1937 0.8022 0.2417
0.500 0.8631 0.01628 0.00877 -0.1936 0.7952 0.2457
0.750 0.9007 0.01568 0.00815 -0.1948 0.7897 0.2510
1.000 0.9220 0.01549 0.00806 -0.1932 0.7803 0.2558
1.250 0.9535 0.01505 0.00762 -0.1933 0.7721 0.2627
1.500 0.9816 0.01459 0.00723 -0.1928 0.7613 0.2704
1.750 1.0047 0.01428 0.00697 -0.1913 0.7476 0.2809
2.000 1.0292 0.01386 0.00663 -0.1901 0.7305 0.2961
2.250 1.0481 0.01353 0.00643 -0.1878 0.7043 0.3190
2.500 1.0666 0.01316 0.00609 -0.1854 0.6497 0.3631
2.750 1.0753 0.01355 0.00588 -0.1809 0.5414 0.4221
3.000 1.0849 0.01434 0.00643 -0.1774 0.5046 0.4835
3.250 1.1021 0.01497 0.00692 -0.1754 0.4849 0.5367
3.500 1.1233 0.01542 0.00733 -0.1741 0.4711 0.5800
3.750 1.1460 0.01573 0.00769 -0.1732 0.4608 0.6234
4.000 1.1688 0.01590 0.00803 -0.1723 0.4529 0.7161
4.250 1.1918 0.01596 0.00828 -0.1712 0.4457 1.0000
4.500 1.2172 0.01641 0.00864 -0.1709 0.4393 1.0000
4.750 1.2439 0.01687 0.00902 -0.1708 0.4338 1.0000
5.000 1.2689 0.01724 0.00939 -0.1703 0.4284 1.0000
5.250 1.2949 0.01767 0.00976 -0.1701 0.4233 1.0000
5.500 1.3220 0.01814 0.01019 -0.1701 0.4182 1.0000
5.750 1.3453 0.01850 0.01060 -0.1693 0.4130 1.0000
6.000 1.3705 0.01891 0.01100 -0.1689 0.4082 1.0000
6.250 1.4005 0.01946 0.01147 -0.1695 0.4039 1.0000
6.500 1.4232 0.01981 0.01194 -0.1686 0.4002 1.0000
6.750 1.4481 0.02022 0.01242 -0.1682 0.3965 1.0000
7.000 1.4732 0.02065 0.01287 -0.1678 0.3921 1.0000
7.250 1.5025 0.02121 0.01339 -0.1683 0.3877 1.0000
7.500 1.5226 0.02158 0.01392 -0.1670 0.3838 1.0000
7.750 1.5428 0.02196 0.01438 -0.1657 0.3783 1.0000
8.000 1.5652 0.02244 0.01482 -0.1648 0.3712 1.0000
8.250 1.5740 0.02271 0.01525 -0.1614 0.3638 1.0000
8.500 1.5921 0.02315 0.01562 -0.1598 0.3557 1.0000
8.750 1.5968 0.02346 0.01611 -0.1557 0.3485 1.0000
9.000 1.6126 0.02392 0.01649 -0.1537 0.3404 1.0000
9.250 1.6167 0.02433 0.01713 -0.1498 0.3332 1.0000
9.500 1.6280 0.02483 0.01761 -0.1472 0.3249 1.0000
9.750 1.6321 0.02537 0.01836 -0.1435 0.3165 1.0000
10.000 1.6399 0.02601 0.01902 -0.1406 0.3077 1.0000
10.250 1.6423 0.02674 0.01990 -0.1370 0.2962 1.0000
10.500 1.6454 0.02759 0.02087 -0.1337 0.2821 1.0000
10.750 1.6462 0.02867 0.02202 -0.1303 0.2620 1.0000
11.000 1.6419 0.03029 0.02351 -0.1267 0.2107 1.0000
11.250 1.6224 0.03360 0.02630 -0.1221 0.1552 1.0000
11.500 1.6058 0.03721 0.02956 -0.1182 0.1030 1.0000
11.750 1.5860 0.04130 0.03325 -0.1145 0.0582 1.0000
12.000 1.5751 0.04476 0.03665 -0.1118 0.0465 1.0000
12.250 1.5701 0.04780 0.03979 -0.1096 0.0416 1.0000
12.500 1.5652 0.05095 0.04305 -0.1077 0.0385 1.0000
12.750 1.5561 0.05469 0.04691 -0.1060 0.0364 1.0000
13.000 1.5489 0.05842 0.05078 -0.1046 0.0351 1.0000
13.250 1.5439 0.06203 0.05456 -0.1036 0.0339 1.0000
13.500 1.5373 0.06602 0.05869 -0.1028 0.0328 1.0000
13.750 1.5299 0.07029 0.06310 -0.1024 0.0319 1.0000
14.000 1.5219 0.07484 0.06777 -0.1023 0.0310 1.0000
14.250 1.5126 0.07973 0.07277 -0.1025 0.0301 1.0000
14.500 1.5028 0.08479 0.07790 -0.1029 0.0293 1.0000
14.750 1.4967 0.08927 0.08244 -0.1031 0.0285 1.0000
15.000 1.4973 0.09295 0.08625 -0.1034 0.0277 1.0000
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