GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 200,000 Max Cl/Cd: 74.11 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe401-il-200000.txt Download as CSV file: xf-goe401-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 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 -0.3143 0.09035 0.08691 -0.0216 1.0000 0.0395
-7.250 -0.3208 0.08919 0.08583 -0.0235 1.0000 0.0405
-7.000 -0.3195 0.08772 0.08441 -0.0295 1.0000 0.0409
-6.750 -0.3131 0.08542 0.08211 -0.0331 1.0000 0.0411
-6.500 -0.3148 0.08079 0.07757 -0.0295 1.0000 0.0415
-6.250 -0.3147 0.07800 0.07484 -0.0258 1.0000 0.0420
-6.000 -0.3186 0.07609 0.07299 -0.0229 1.0000 0.0425
-5.750 -0.3140 0.07383 0.07076 -0.0225 0.9986 0.0432
-5.500 -0.2781 0.06962 0.06650 -0.0294 0.9929 0.0452
-5.250 -0.2024 0.06586 0.06233 -0.0503 0.9839 0.0505
-5.000 -0.1859 0.05986 0.05641 -0.0516 0.9766 0.0514
-4.750 -0.1579 0.05618 0.05275 -0.0541 0.9717 0.0527
-4.500 -0.1275 0.05305 0.04957 -0.0575 0.9624 0.0550
-4.250 -0.0633 0.05136 0.04736 -0.0683 0.9533 0.0615
-4.000 -0.0401 0.04549 0.04158 -0.0709 0.9469 0.0629
-3.750 -0.0116 0.04266 0.03876 -0.0729 0.9389 0.0651
-3.500 0.0281 0.03993 0.03591 -0.0770 0.9320 0.0693
-3.250 0.0750 0.03714 0.03268 -0.0820 0.9219 0.0755
-3.000 0.1080 0.03413 0.02969 -0.0847 0.9136 0.0777
-2.750 0.1429 0.03203 0.02748 -0.0870 0.9016 0.0820
-2.500 0.1815 0.03024 0.02525 -0.0891 0.8877 0.0901
-2.250 0.2075 0.02815 0.02316 -0.0897 0.8727 0.0932
-1.750 0.2633 0.02535 0.01989 -0.0896 0.8407 0.1065
-1.500 0.2876 0.02401 0.01844 -0.0891 0.8241 0.1105
-1.250 0.3149 0.02317 0.01725 -0.0883 0.8074 0.1208
-1.000 0.3382 0.02173 0.01574 -0.0875 0.7900 0.1243
-0.750 0.3711 0.01806 0.01116 -0.0855 0.7751 0.0720
-0.500 0.3960 0.01663 0.00947 -0.0844 0.7561 0.0689
-0.250 0.4214 0.01561 0.00816 -0.0832 0.7357 0.0683
0.000 0.4471 0.01452 0.00671 -0.0820 0.7147 0.0657
0.250 0.4720 0.01385 0.00584 -0.0808 0.6909 0.0650
0.500 0.4965 0.01339 0.00521 -0.0796 0.6662 0.0656
0.750 0.5204 0.01305 0.00475 -0.0784 0.6393 0.0672
1.000 0.5442 0.01282 0.00439 -0.0772 0.6140 0.0696
1.250 0.5681 0.01272 0.00413 -0.0761 0.5906 0.0735
1.500 0.5918 0.01258 0.00395 -0.0750 0.5701 0.0818
1.750 0.6157 0.01248 0.00380 -0.0740 0.5519 0.0949
2.000 0.6395 0.01235 0.00379 -0.0730 0.5363 0.1725
2.250 0.6632 0.01228 0.00380 -0.0721 0.5228 0.2448
2.500 0.7281 0.01107 0.00390 -0.0804 0.5057 1.0000
2.750 0.7527 0.01136 0.00400 -0.0796 0.4949 1.0000
3.000 0.7774 0.01160 0.00414 -0.0788 0.4841 1.0000
3.250 0.8022 0.01187 0.00433 -0.0781 0.4742 1.0000
3.750 0.8517 0.01244 0.00473 -0.0767 0.4559 1.0000
4.000 0.8767 0.01277 0.00497 -0.0760 0.4476 1.0000
4.250 0.9012 0.01303 0.00522 -0.0753 0.4385 1.0000
4.500 0.9260 0.01336 0.00551 -0.0747 0.4304 1.0000
4.750 0.9506 0.01366 0.00578 -0.0740 0.4222 1.0000
5.000 0.9750 0.01397 0.00610 -0.0733 0.4134 1.0000
5.250 0.9992 0.01428 0.00635 -0.0725 0.4043 1.0000
5.500 1.0227 0.01452 0.00665 -0.0717 0.3944 1.0000
5.750 1.0467 0.01484 0.00693 -0.0709 0.3856 1.0000
6.000 1.0702 0.01507 0.00723 -0.0700 0.3761 1.0000
6.250 1.0938 0.01536 0.00755 -0.0692 0.3675 1.0000
6.500 1.1171 0.01561 0.00781 -0.0683 0.3585 1.0000
6.750 1.1400 0.01585 0.00816 -0.0673 0.3489 1.0000
7.000 1.1636 0.01618 0.00845 -0.0666 0.3413 1.0000
7.250 1.1860 0.01639 0.00882 -0.0655 0.3317 1.0000
7.500 1.2080 0.01660 0.00908 -0.0644 0.3212 1.0000
7.750 1.2290 0.01677 0.00930 -0.0632 0.3089 1.0000
8.000 1.2494 0.01693 0.00951 -0.0618 0.2944 1.0000
8.250 1.2695 0.01713 0.00978 -0.0605 0.2785 1.0000
8.500 1.2895 0.01740 0.01011 -0.0592 0.2616 1.0000
8.750 1.3081 0.01777 0.01049 -0.0577 0.2406 1.0000
9.000 1.3251 0.01829 0.01101 -0.0560 0.2126 1.0000
9.250 1.3348 0.01942 0.01182 -0.0534 0.1523 1.0000
9.500 1.3302 0.02184 0.01360 -0.0492 0.0793 1.0000
9.750 1.3301 0.02373 0.01543 -0.0453 0.0626 1.0000
10.000 1.3235 0.02563 0.01736 -0.0405 0.0545 1.0000
10.250 1.3247 0.02700 0.01886 -0.0368 0.0491 1.0000
10.500 1.3222 0.02866 0.02056 -0.0332 0.0457 1.0000
10.750 1.3145 0.03086 0.02280 -0.0296 0.0432 1.0000
11.000 1.3194 0.03233 0.02443 -0.0276 0.0403 1.0000
11.250 1.3208 0.03419 0.02637 -0.0256 0.0385 1.0000
11.500 1.3206 0.03632 0.02854 -0.0239 0.0367 1.0000
11.750 1.3184 0.03887 0.03109 -0.0222 0.0354 1.0000
12.000 1.3214 0.04115 0.03345 -0.0207 0.0343 1.0000
12.250 1.3271 0.04313 0.03557 -0.0196 0.0331 1.0000
12.500 1.3326 0.04521 0.03775 -0.0185 0.0319 1.0000
12.750 1.3368 0.04738 0.04003 -0.0178 0.0306 1.0000
13.000 1.3408 0.04963 0.04234 -0.0171 0.0296 1.0000
13.250 1.3467 0.05188 0.04462 -0.0163 0.0287 1.0000
13.500 1.3618 0.05427 0.04703 -0.0144 0.0277 1.0000
13.750 1.3644 0.05694 0.04991 -0.0138 0.0274 1.0000
14.000 1.3669 0.05980 0.05297 -0.0132 0.0271 1.0000
14.250 1.3669 0.06304 0.05643 -0.0129 0.0268 1.0000
14.500 1.3633 0.06668 0.06031 -0.0128 0.0265 1.0000
14.750 1.3580 0.07062 0.06448 -0.0131 0.0263 1.0000
15.000 1.3498 0.07487 0.06895 -0.0139 0.0261 1.0000
15.250 1.3389 0.07957 0.07387 -0.0151 0.0258 1.0000
15.500 1.3267 0.08462 0.07914 -0.0169 0.0256 1.0000
15.750 1.3133 0.09000 0.08473 -0.0191 0.0254 1.0000
16.000 1.2962 0.09643 0.09139 -0.0219 0.0255 1.0000
16.250 1.2792 0.10305 0.09822 -0.0252 0.0256 1.0000
16.500 1.2608 0.11020 0.10557 -0.0291 0.0256 1.0000
16.750 1.2403 0.11814 0.11371 -0.0338 0.0257 1.0000
17.000 1.2190 0.12666 0.12242 -0.0390 0.0260 1.0000
17.250 1.1962 0.13597 0.13190 -0.0448 0.0263 1.0000
17.500 1.1739 0.14573 0.14180 -0.0511 0.0267 1.0000
17.750 1.1538 0.15543 0.15160 -0.0570 0.0273 1.0000
18.000 1.1333 0.16586 0.16212 -0.0635 0.0276 1.0000
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