GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 420 AIRFOIL (goe420-il) Reynolds number: 100,000 Max Cl/Cd: 44.46 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe420-il-100000-n5.txt Download as CSV file: xf-goe420-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 420 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5285 0.06452 0.05801 -0.1035 0.9736 0.0534
-12.250 -0.5416 0.05778 0.05099 -0.1111 0.9668 0.0536
-12.000 -0.5470 0.05322 0.04620 -0.1159 0.9583 0.0539
-11.750 -0.5421 0.04934 0.04208 -0.1207 0.9523 0.0543
-11.500 -0.5376 0.04630 0.03884 -0.1236 0.9444 0.0548
-11.250 -0.5281 0.04366 0.03598 -0.1262 0.9374 0.0553
-11.000 -0.5167 0.04143 0.03354 -0.1279 0.9311 0.0559
-10.750 -0.5106 0.03977 0.03170 -0.1274 0.9220 0.0564
-10.500 -0.4938 0.03797 0.02968 -0.1284 0.9165 0.0572
-10.250 -0.4881 0.03677 0.02830 -0.1266 0.9071 0.0578
-10.000 -0.4684 0.03548 0.02695 -0.1268 0.9012 0.0586
-9.750 -0.4433 0.03428 0.02574 -0.1277 0.8972 0.0598
-9.500 -0.4369 0.03358 0.02500 -0.1253 0.8878 0.0607
-9.250 -0.4184 0.03258 0.02390 -0.1249 0.8820 0.0622
-9.000 -0.3944 0.03148 0.02264 -0.1253 0.8779 0.0641
-8.750 -0.3883 0.03091 0.02203 -0.1223 0.8681 0.0652
-8.500 -0.3691 0.03003 0.02116 -0.1217 0.8625 0.0668
-8.250 -0.3454 0.02911 0.02018 -0.1217 0.8585 0.0687
-8.000 -0.3399 0.02869 0.01972 -0.1185 0.8490 0.0702
-7.750 -0.3210 0.02793 0.01889 -0.1175 0.8435 0.0726
-7.500 -0.2986 0.02707 0.01801 -0.1173 0.8395 0.0755
-7.250 -0.2910 0.02669 0.01759 -0.1143 0.8302 0.0786
-7.000 -0.2726 0.02597 0.01686 -0.1133 0.8245 0.0829
-6.750 -0.2489 0.02521 0.01604 -0.1130 0.8207 0.0892
-6.500 -0.2385 0.02479 0.01567 -0.1105 0.8128 0.0951
-6.250 -0.2199 0.02421 0.01513 -0.1093 0.8066 0.1047
-6.000 -0.1948 0.02355 0.01449 -0.1091 0.8025 0.1214
-5.750 -0.1752 0.02309 0.01404 -0.1080 0.7967 0.1409
-5.500 -0.1585 0.02273 0.01369 -0.1063 0.7889 0.1596
-5.250 -0.1317 0.02209 0.01311 -0.1063 0.7837 0.1823
-5.000 -0.1102 0.02170 0.01280 -0.1052 0.7764 0.2055
-4.750 -0.0891 0.02143 0.01259 -0.1040 0.7684 0.2302
-4.500 -0.0589 0.02109 0.01223 -0.1043 0.7635 0.2576
-4.250 -0.0386 0.02106 0.01217 -0.1030 0.7564 0.2788
-4.000 -0.0158 0.02100 0.01208 -0.1020 0.7499 0.2985
-3.750 0.0132 0.02083 0.01187 -0.1020 0.7454 0.3190
-3.500 0.0378 0.02078 0.01178 -0.1013 0.7399 0.3370
-3.250 0.0575 0.02080 0.01184 -0.0998 0.7326 0.3498
-3.000 0.0864 0.02061 0.01157 -0.0998 0.7277 0.3624
-2.750 0.1177 0.02038 0.01126 -0.1001 0.7236 0.3740
-2.500 0.1341 0.02046 0.01134 -0.0981 0.7151 0.3829
-2.250 0.1625 0.02029 0.01111 -0.0980 0.7098 0.3936
-2.000 0.1954 0.02003 0.01078 -0.0986 0.7059 0.4039
-1.750 0.2117 0.02015 0.01091 -0.0965 0.6976 0.4125
-1.500 0.2394 0.02001 0.01072 -0.0963 0.6918 0.4228
-1.250 0.2725 0.01977 0.01041 -0.0969 0.6875 0.4341
-1.000 0.2894 0.01987 0.01055 -0.0950 0.6789 0.4442
-0.750 0.3174 0.01975 0.01038 -0.0948 0.6728 0.4580
-0.500 0.3497 0.01952 0.01014 -0.0953 0.6682 0.4718
-0.250 0.3664 0.01966 0.01032 -0.0933 0.6596 0.4838
0.000 0.3946 0.01953 0.01018 -0.0932 0.6536 0.4975
0.250 0.4241 0.01938 0.01003 -0.0932 0.6481 0.5111
0.500 0.4429 0.01947 0.01016 -0.0916 0.6394 0.5238
0.750 0.4728 0.01932 0.01000 -0.0917 0.6332 0.5382
1.000 0.4963 0.01933 0.01006 -0.0908 0.6259 0.5533
1.250 0.5189 0.01936 0.01015 -0.0897 0.6182 0.5712
1.500 0.5496 0.01924 0.01003 -0.0899 0.6127 0.5929
1.750 0.5677 0.01939 0.01027 -0.0881 0.6044 0.6152
2.000 0.5925 0.01940 0.01031 -0.0874 0.5972 0.6417
2.250 0.6205 0.01933 0.01026 -0.0871 0.5910 0.6718
2.750 0.6628 0.01938 0.01053 -0.0842 0.5759 0.7425
3.000 0.6835 0.01943 0.01080 -0.0825 0.5689 0.7966
3.250 0.7158 0.01953 0.01105 -0.0830 0.5612 0.8867
3.500 0.7722 0.01953 0.01096 -0.0883 0.5551 0.9658
3.750 0.7939 0.01991 0.01135 -0.0878 0.5464 1.0000
4.000 0.8164 0.02009 0.01142 -0.0870 0.5402 1.0000
4.250 0.8382 0.02031 0.01155 -0.0860 0.5341 1.0000
4.500 0.8530 0.02066 0.01187 -0.0839 0.5267 1.0000
4.750 0.8779 0.02082 0.01193 -0.0834 0.5209 1.0000
5.000 0.8950 0.02116 0.01223 -0.0817 0.5142 1.0000
5.250 0.9113 0.02146 0.01251 -0.0798 0.5071 1.0000
5.500 0.9394 0.02158 0.01250 -0.0798 0.5014 1.0000
5.750 0.9477 0.02206 0.01300 -0.0767 0.4942 1.0000
6.000 0.9667 0.02236 0.01326 -0.0753 0.4879 1.0000
6.250 0.9955 0.02252 0.01331 -0.0755 0.4828 1.0000
6.500 1.0036 0.02311 0.01395 -0.0725 0.4763 1.0000
6.750 1.0225 0.02348 0.01431 -0.0712 0.4705 1.0000
7.000 1.0519 0.02366 0.01440 -0.0715 0.4658 1.0000
7.250 1.0617 0.02430 0.01509 -0.0689 0.4599 1.0000
7.500 1.0774 0.02482 0.01563 -0.0673 0.4544 1.0000
7.750 1.1020 0.02513 0.01590 -0.0669 0.4496 1.0000
8.000 1.1229 0.02557 0.01632 -0.0660 0.4446 1.0000
8.250 1.1309 0.02633 0.01716 -0.0635 0.4385 1.0000
8.500 1.1502 0.02678 0.01761 -0.0624 0.4331 1.0000
8.750 1.1818 0.02697 0.01772 -0.0630 0.4287 1.0000
9.000 1.1837 0.02797 0.01885 -0.0598 0.4230 1.0000
9.250 1.1953 0.02872 0.01966 -0.0580 0.4173 1.0000
9.500 1.2192 0.02907 0.01999 -0.0575 0.4122 1.0000
9.750 1.2345 0.02974 0.02069 -0.0561 0.4070 1.0000
10.000 1.2348 0.03091 0.02198 -0.0532 0.4004 1.0000
10.250 1.2535 0.03133 0.02237 -0.0522 0.3938 1.0000
10.500 1.2584 0.03234 0.02345 -0.0498 0.3867 1.0000
10.750 1.2587 0.03353 0.02470 -0.0471 0.3784 1.0000
11.000 1.2682 0.03427 0.02542 -0.0453 0.3701 1.0000
11.250 1.2609 0.03599 0.02724 -0.0423 0.3609 1.0000
11.500 1.2677 0.03697 0.02822 -0.0406 0.3524 1.0000
11.750 1.2606 0.03900 0.03037 -0.0382 0.3436 1.0000
12.000 1.2685 0.04009 0.03146 -0.0367 0.3359 1.0000
12.250 1.2606 0.04251 0.03402 -0.0348 0.3276 1.0000
12.500 1.2729 0.04338 0.03485 -0.0337 0.3208 1.0000
12.750 1.2601 0.04650 0.03814 -0.0320 0.3120 1.0000
13.000 1.2709 0.04755 0.03917 -0.0311 0.3049 1.0000
13.250 1.2587 0.05096 0.04274 -0.0299 0.2962 1.0000
13.500 1.2686 0.05219 0.04393 -0.0291 0.2889 1.0000
13.750 1.2573 0.05580 0.04767 -0.0283 0.2802 1.0000
14.000 1.2670 0.05711 0.04895 -0.0277 0.2727 1.0000
14.250 1.2554 0.06102 0.05298 -0.0273 0.2639 1.0000
14.500 1.2642 0.06250 0.05442 -0.0267 0.2560 1.0000
14.750 1.2518 0.06673 0.05877 -0.0267 0.2469 1.0000
15.000 1.2566 0.06881 0.06082 -0.0263 0.2387 1.0000
15.250 1.2473 0.07286 0.06498 -0.0265 0.2298 1.0000
15.500 1.2483 0.07555 0.06766 -0.0265 0.2214 1.0000
15.750 1.2418 0.07938 0.07155 -0.0268 0.2122 1.0000
16.000 1.2376 0.08296 0.07517 -0.0272 0.2032 1.0000
16.250 1.2366 0.08609 0.07829 -0.0276 0.1941 1.0000
16.500 1.2270 0.09067 0.08297 -0.0285 0.1843 1.0000
16.750 1.2246 0.09413 0.08643 -0.0291 0.1754 1.0000
17.000 1.2210 0.09785 0.09016 -0.0299 0.1665 1.0000
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Polar data table (+)
Polar graphs
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