GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 404 AIRFOIL (goe404-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.67 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe404-il-1000000-n5.txt Download as CSV file: xf-goe404-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 404 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.4756 0.18067 0.17873 0.0038 1.0000 0.0153
-16.500 -0.4659 0.17821 0.17627 0.0024 1.0000 0.0154
-13.500 -0.9258 0.03202 0.02881 -0.0946 0.9884 0.0230
-13.250 -0.9080 0.02907 0.02566 -0.0967 0.9797 0.0231
-13.000 -0.8886 0.02707 0.02349 -0.0976 0.9705 0.0232
-12.750 -0.8687 0.02549 0.02176 -0.0979 0.9617 0.0233
-12.250 -0.8279 0.02305 0.01905 -0.0973 0.9451 0.0235
-12.000 -0.8067 0.02205 0.01793 -0.0968 0.9372 0.0236
-11.750 -0.7846 0.02114 0.01690 -0.0963 0.9296 0.0236
-11.500 -0.7621 0.02032 0.01597 -0.0957 0.9213 0.0237
-11.250 -0.7387 0.01957 0.01511 -0.0952 0.9137 0.0238
-11.000 -0.7149 0.01888 0.01432 -0.0947 0.9054 0.0238
-10.750 -0.6907 0.01825 0.01358 -0.0942 0.8982 0.0239
-10.500 -0.6672 0.01740 0.01264 -0.0937 0.8893 0.0241
-10.250 -0.6433 0.01670 0.01183 -0.0932 0.8789 0.0242
-10.000 -0.6188 0.01611 0.01113 -0.0926 0.8641 0.0244
-9.750 -0.5940 0.01560 0.01051 -0.0920 0.8453 0.0245
-9.500 -0.5688 0.01516 0.00994 -0.0914 0.8219 0.0247
-9.250 -0.5438 0.01479 0.00941 -0.0908 0.7894 0.0249
-9.000 -0.5186 0.01449 0.00893 -0.0901 0.7542 0.0250
-8.750 -0.4928 0.01419 0.00847 -0.0896 0.7279 0.0252
-8.500 -0.4664 0.01389 0.00805 -0.0892 0.7091 0.0254
-8.250 -0.4396 0.01357 0.00764 -0.0889 0.6958 0.0256
-8.000 -0.4125 0.01326 0.00725 -0.0886 0.6847 0.0257
-7.750 -0.3853 0.01298 0.00688 -0.0882 0.6737 0.0260
-7.500 -0.3579 0.01269 0.00652 -0.0880 0.6645 0.0262
-7.250 -0.3304 0.01243 0.00619 -0.0877 0.6548 0.0264
-7.000 -0.3026 0.01218 0.00588 -0.0875 0.6474 0.0267
-6.750 -0.2748 0.01195 0.00559 -0.0872 0.6388 0.0269
-6.500 -0.2470 0.01174 0.00531 -0.0870 0.6304 0.0271
-6.250 -0.2190 0.01152 0.00504 -0.0867 0.6220 0.0273
-6.000 -0.1913 0.01129 0.00475 -0.0865 0.6141 0.0275
-5.750 -0.1634 0.01102 0.00444 -0.0863 0.6073 0.0279
-5.500 -0.1354 0.01080 0.00418 -0.0860 0.5987 0.0283
-5.250 -0.1074 0.01062 0.00395 -0.0858 0.5901 0.0286
-5.000 -0.0793 0.01045 0.00374 -0.0856 0.5802 0.0290
-4.750 -0.0512 0.01031 0.00355 -0.0854 0.5711 0.0294
-4.500 -0.0229 0.01017 0.00337 -0.0852 0.5609 0.0299
-4.250 0.0052 0.01005 0.00320 -0.0850 0.5508 0.0303
-4.000 0.0333 0.00996 0.00305 -0.0848 0.5384 0.0308
-3.750 0.0614 0.00986 0.00290 -0.0846 0.5241 0.0313
-3.500 0.0893 0.00977 0.00275 -0.0843 0.5072 0.0322
-3.250 0.1170 0.00972 0.00262 -0.0840 0.4887 0.0331
-3.000 0.1448 0.00969 0.00252 -0.0838 0.4721 0.0342
-2.750 0.1727 0.00965 0.00243 -0.0836 0.4581 0.0358
-2.500 0.2004 0.00961 0.00233 -0.0833 0.4453 0.0386
-2.250 0.2284 0.00952 0.00225 -0.0831 0.4349 0.0441
-2.000 0.2562 0.00947 0.00221 -0.0829 0.4257 0.0546
-1.750 0.2845 0.00945 0.00220 -0.0828 0.4176 0.0615
-1.250 0.3411 0.00948 0.00219 -0.0825 0.4026 0.0689
-1.000 0.3694 0.00951 0.00219 -0.0823 0.3951 0.0717
-0.750 0.3976 0.00955 0.00219 -0.0822 0.3880 0.0735
-0.500 0.4260 0.00956 0.00220 -0.0821 0.3813 0.0765
-0.250 0.4541 0.00960 0.00222 -0.0819 0.3743 0.0791
0.000 0.4825 0.00964 0.00224 -0.0818 0.3691 0.0811
0.250 0.5108 0.00964 0.00223 -0.0817 0.3637 0.0828
0.500 0.5389 0.00968 0.00226 -0.0815 0.3578 0.0850
0.750 0.5670 0.00972 0.00228 -0.0814 0.3523 0.0871
1.000 0.5953 0.00974 0.00231 -0.0813 0.3478 0.0891
1.250 0.6235 0.00979 0.00234 -0.0811 0.3426 0.0911
1.500 0.6514 0.00983 0.00237 -0.0810 0.3376 0.0941
1.750 0.6795 0.00987 0.00241 -0.0809 0.3338 0.0963
2.000 0.7077 0.00990 0.00245 -0.0808 0.3299 0.0985
2.250 0.7357 0.00995 0.00249 -0.0806 0.3254 0.1006
2.500 0.7634 0.01003 0.00255 -0.0805 0.3204 0.1037
2.750 0.7913 0.01008 0.00262 -0.0803 0.3166 0.1079
3.000 0.8193 0.01013 0.00268 -0.0802 0.3129 0.1127
3.250 0.8470 0.01018 0.00275 -0.0801 0.3083 0.1216
3.500 0.8745 0.01025 0.00285 -0.0800 0.3041 0.1370
3.750 0.9019 0.01028 0.00296 -0.0798 0.3001 0.1788
4.000 0.9294 0.01028 0.00306 -0.0797 0.2955 0.2268
4.250 0.9518 0.00939 0.00331 -0.0791 0.2883 0.7277
4.750 1.0156 0.00921 0.00363 -0.0806 0.2717 1.0000
5.000 1.0414 0.00941 0.00376 -0.0802 0.2630 1.0000
5.250 1.0668 0.00965 0.00392 -0.0797 0.2521 1.0000
5.500 1.0916 0.00992 0.00411 -0.0791 0.2375 1.0000
5.750 1.1146 0.01035 0.00438 -0.0783 0.2120 1.0000
6.000 1.1349 0.01100 0.00481 -0.0771 0.1789 1.0000
6.500 1.1829 0.01167 0.00536 -0.0759 0.1606 1.0000
6.750 1.2069 0.01199 0.00563 -0.0752 0.1543 1.0000
7.000 1.2316 0.01225 0.00587 -0.0747 0.1502 1.0000
7.250 1.2564 0.01249 0.00610 -0.0742 0.1473 1.0000
7.500 1.2807 0.01276 0.00636 -0.0737 0.1441 1.0000
7.750 1.3045 0.01307 0.00663 -0.0731 0.1407 1.0000
8.000 1.3285 0.01334 0.00691 -0.0725 0.1377 1.0000
8.250 1.3527 0.01359 0.00716 -0.0719 0.1358 1.0000
8.500 1.3764 0.01386 0.00742 -0.0713 0.1333 1.0000
8.750 1.3995 0.01415 0.00771 -0.0706 0.1308 1.0000
9.000 1.4220 0.01448 0.00803 -0.0699 0.1281 1.0000
9.250 1.4438 0.01483 0.00837 -0.0690 0.1252 1.0000
9.500 1.4664 0.01511 0.00867 -0.0683 0.1235 1.0000
9.750 1.4877 0.01544 0.00900 -0.0673 0.1206 1.0000
10.000 1.5068 0.01581 0.00937 -0.0660 0.1174 1.0000
10.250 1.5248 0.01623 0.00978 -0.0646 0.1143 1.0000
10.500 1.5435 0.01662 0.01018 -0.0633 0.1120 1.0000
10.750 1.5619 0.01703 0.01061 -0.0621 0.1092 1.0000
11.000 1.5787 0.01754 0.01111 -0.0607 0.1054 1.0000
11.250 1.5944 0.01812 0.01168 -0.0592 0.1014 1.0000
11.500 1.6099 0.01873 0.01230 -0.0578 0.0963 1.0000
11.750 1.6220 0.01956 0.01309 -0.0560 0.0887 1.0000
12.000 1.6244 0.02103 0.01445 -0.0534 0.0716 1.0000
12.250 1.6290 0.02244 0.01582 -0.0513 0.0633 1.0000
12.500 1.6376 0.02366 0.01706 -0.0497 0.0599 1.0000
12.750 1.6482 0.02480 0.01823 -0.0484 0.0583 1.0000
13.000 1.6579 0.02605 0.01951 -0.0472 0.0569 1.0000
13.250 1.6660 0.02748 0.02099 -0.0461 0.0556 1.0000
13.500 1.6731 0.02908 0.02263 -0.0451 0.0542 1.0000
13.750 1.6810 0.03068 0.02428 -0.0442 0.0532 1.0000
14.000 1.6887 0.03235 0.02601 -0.0435 0.0524 1.0000
14.250 1.6952 0.03420 0.02791 -0.0429 0.0516 1.0000
14.500 1.7005 0.03621 0.02999 -0.0424 0.0510 1.0000
14.750 1.7043 0.03841 0.03225 -0.0419 0.0504 1.0000
15.000 1.7065 0.04081 0.03472 -0.0415 0.0499 1.0000
15.250 1.7071 0.04344 0.03741 -0.0412 0.0492 1.0000
15.500 1.7062 0.04628 0.04032 -0.0409 0.0486 1.0000
15.750 1.7041 0.04931 0.04342 -0.0408 0.0480 1.0000
16.000 1.7010 0.05253 0.04672 -0.0408 0.0475 1.0000
16.250 1.6992 0.05566 0.04993 -0.0409 0.0473 1.0000
16.500 1.6971 0.05885 0.05320 -0.0410 0.0471 1.0000
16.750 1.6942 0.06221 0.05665 -0.0413 0.0468 1.0000
17.000 1.6903 0.06575 0.06029 -0.0416 0.0466 1.0000
17.250 1.6856 0.06945 0.06407 -0.0421 0.0463 1.0000
17.500 1.6799 0.07331 0.06802 -0.0427 0.0460 1.0000
17.750 1.6734 0.07733 0.07213 -0.0433 0.0457 1.0000
18.000 1.6664 0.08147 0.07635 -0.0441 0.0454 1.0000
18.250 1.6588 0.08567 0.08064 -0.0449 0.0452 1.0000
18.500 1.6515 0.08984 0.08490 -0.0457 0.0449 1.0000
18.750 1.6434 0.09419 0.08933 -0.0467 0.0446 1.0000
19.000 1.6347 0.09867 0.09390 -0.0478 0.0443 1.0000
19.250 1.6274 0.10289 0.09819 -0.0489 0.0440 1.0000
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Polar data table (+)
Polar graphs
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