GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 432 AIRFOIL (goe432-il) Reynolds number: 200,000 Max Cl/Cd: 72.55 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe432-il-200000.txt Download as CSV file: xf-goe432-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 432 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 -0.3617 0.08847 0.08514 -0.0209 1.0000 0.0383
-7.250 -0.3680 0.08651 0.08325 -0.0194 1.0000 0.0388
-7.000 -0.3713 0.08419 0.08098 -0.0189 1.0000 0.0395
-6.750 -0.3725 0.08156 0.07839 -0.0191 1.0000 0.0404
-6.500 -0.3723 0.07882 0.07568 -0.0199 1.0000 0.0414
-6.250 -0.3698 0.07585 0.07274 -0.0216 1.0000 0.0426
-6.000 -0.3568 0.07227 0.06910 -0.0293 1.0000 0.0446
-5.750 -0.3410 0.06840 0.06511 -0.0347 1.0000 0.0451
-5.500 -0.3313 0.06352 0.06014 -0.0370 1.0000 0.0454
-5.250 -0.3318 0.05928 0.05600 -0.0347 1.0000 0.0463
-5.000 -0.3260 0.05701 0.05377 -0.0327 1.0000 0.0473
-4.750 -0.3173 0.05501 0.05177 -0.0314 1.0000 0.0490
-4.500 -0.2952 0.05183 0.04851 -0.0339 0.9988 0.0524
-4.250 -0.2369 0.04373 0.03981 -0.0461 0.9942 0.0588
-4.000 -0.2057 0.04074 0.03685 -0.0488 0.9889 0.0611
-3.750 -0.1490 0.03878 0.03408 -0.0552 0.9837 0.0713
-3.500 -0.1237 0.03330 0.02885 -0.0578 0.9779 0.0753
-3.250 -0.0821 0.03058 0.02584 -0.0617 0.9727 0.0890
-3.000 -0.0445 0.02824 0.02321 -0.0644 0.9667 0.1031
-2.750 0.0008 0.02175 0.01522 -0.0644 0.9623 0.0579
-2.500 0.0405 0.01875 0.01181 -0.0666 0.9584 0.0594
-2.250 0.0771 0.01763 0.01063 -0.0683 0.9516 0.0653
-2.000 0.1173 0.01656 0.00928 -0.0701 0.9452 0.0699
-1.750 0.1593 0.01526 0.00792 -0.0726 0.9399 0.0763
-1.500 0.1976 0.01444 0.00706 -0.0741 0.9305 0.0821
-1.250 0.2367 0.01349 0.00611 -0.0757 0.9216 0.0881
-1.000 0.2784 0.01269 0.00537 -0.0779 0.9132 0.0966
-0.750 0.3110 0.01199 0.00473 -0.0783 0.8994 0.1064
-0.500 0.3445 0.01135 0.00413 -0.0787 0.8827 0.1231
-0.250 0.4078 0.00854 0.00381 -0.0860 0.8675 1.0000
0.000 0.4450 0.00836 0.00338 -0.0871 0.8406 1.0000
0.250 0.4783 0.00831 0.00308 -0.0875 0.8062 1.0000
0.500 0.5076 0.00840 0.00289 -0.0872 0.7664 1.0000
0.750 0.5327 0.00860 0.00281 -0.0861 0.7229 1.0000
1.000 0.5561 0.00886 0.00278 -0.0847 0.6800 1.0000
1.250 0.5789 0.00914 0.00279 -0.0834 0.6413 1.0000
1.500 0.6019 0.00944 0.00284 -0.0821 0.6090 1.0000
1.750 0.6253 0.00974 0.00293 -0.0810 0.5838 1.0000
2.000 0.6491 0.01004 0.00304 -0.0800 0.5624 1.0000
2.250 0.6733 0.01034 0.00318 -0.0791 0.5447 1.0000
2.500 0.6977 0.01064 0.00334 -0.0783 0.5285 1.0000
2.750 0.7222 0.01091 0.00353 -0.0775 0.5129 1.0000
3.000 0.7467 0.01118 0.00370 -0.0767 0.4984 1.0000
3.250 0.7715 0.01142 0.00389 -0.0760 0.4848 1.0000
3.500 0.7962 0.01165 0.00409 -0.0752 0.4716 1.0000
3.750 0.8209 0.01187 0.00431 -0.0745 0.4587 1.0000
4.000 0.8454 0.01210 0.00451 -0.0737 0.4455 1.0000
4.250 0.8695 0.01231 0.00470 -0.0729 0.4306 1.0000
4.500 0.8933 0.01252 0.00488 -0.0720 0.4140 1.0000
4.750 0.9167 0.01275 0.00509 -0.0711 0.3967 1.0000
5.000 0.9398 0.01301 0.00531 -0.0701 0.3781 1.0000
5.250 0.9627 0.01327 0.00555 -0.0691 0.3555 1.0000
5.500 0.9848 0.01362 0.00582 -0.0679 0.3304 1.0000
5.750 1.0062 0.01405 0.00617 -0.0667 0.3036 1.0000
6.000 1.0279 0.01451 0.00654 -0.0656 0.2790 1.0000
6.250 1.0497 0.01501 0.00694 -0.0645 0.2609 1.0000
6.500 1.0718 0.01550 0.00739 -0.0635 0.2470 1.0000
6.750 1.0943 0.01598 0.00787 -0.0626 0.2361 1.0000
7.000 1.1169 0.01647 0.00839 -0.0616 0.2271 1.0000
7.250 1.1385 0.01709 0.00894 -0.0606 0.2195 1.0000
7.500 1.1613 0.01758 0.00955 -0.0598 0.2119 1.0000
7.750 1.1830 0.01829 0.01022 -0.0588 0.2049 1.0000
8.000 1.2047 0.01884 0.01086 -0.0578 0.1964 1.0000
8.250 1.2247 0.01948 0.01151 -0.0567 0.1850 1.0000
8.500 1.2436 0.02014 0.01217 -0.0554 0.1730 1.0000
8.750 1.2625 0.02092 0.01293 -0.0542 0.1628 1.0000
9.000 1.2820 0.02130 0.01351 -0.0530 0.1537 1.0000
9.250 1.3006 0.02185 0.01416 -0.0516 0.1448 1.0000
9.500 1.3187 0.02225 0.01464 -0.0502 0.1352 1.0000
9.750 1.3387 0.02234 0.01497 -0.0490 0.1224 1.0000
10.000 1.3582 0.02256 0.01518 -0.0478 0.0921 1.0000
10.250 1.3607 0.02450 0.01680 -0.0444 0.0533 1.0000
10.500 1.3621 0.02625 0.01846 -0.0407 0.0422 1.0000
10.750 1.3648 0.02769 0.02001 -0.0372 0.0377 1.0000
11.000 1.3645 0.02932 0.02171 -0.0337 0.0345 1.0000
11.250 1.3582 0.03141 0.02386 -0.0298 0.0325 1.0000
11.500 1.3610 0.03301 0.02564 -0.0272 0.0308 1.0000
11.750 1.3606 0.03495 0.02774 -0.0247 0.0294 1.0000
12.000 1.3596 0.03707 0.02997 -0.0225 0.0284 1.0000
12.250 1.3570 0.03948 0.03248 -0.0207 0.0273 1.0000
12.500 1.3537 0.04218 0.03527 -0.0192 0.0266 1.0000
12.750 1.3502 0.04519 0.03836 -0.0179 0.0258 1.0000
13.000 1.3483 0.04852 0.04178 -0.0166 0.0250 1.0000
13.250 1.3481 0.05124 0.04471 -0.0162 0.0244 1.0000
13.500 1.3470 0.05426 0.04792 -0.0160 0.0238 1.0000
13.750 1.3446 0.05757 0.05140 -0.0160 0.0230 1.0000
14.000 1.3420 0.06111 0.05512 -0.0162 0.0226 1.0000
14.250 1.3381 0.06493 0.05910 -0.0167 0.0222 1.0000
14.500 1.3326 0.06909 0.06345 -0.0176 0.0219 1.0000
14.750 1.3255 0.07360 0.06815 -0.0189 0.0217 1.0000
15.000 1.3163 0.07859 0.07334 -0.0206 0.0216 1.0000
15.250 1.3053 0.08400 0.07896 -0.0228 0.0214 1.0000
15.500 1.2928 0.08988 0.08504 -0.0255 0.0214 1.0000
15.750 1.2783 0.09637 0.09174 -0.0287 0.0214 1.0000
16.000 1.2612 0.10361 0.09920 -0.0328 0.0215 1.0000
16.250 1.2418 0.11167 0.10745 -0.0375 0.0216 1.0000
16.500 1.2205 0.12062 0.11661 -0.0431 0.0219 1.0000
16.750 1.1968 0.13066 0.12685 -0.0495 0.0222 1.0000
17.000 1.1690 0.14242 0.13881 -0.0573 0.0227 1.0000
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Polar data table (+)
Polar graphs
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