GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 100,000 Max Cl/Cd: 55.95 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe401-il-100000-n5.txt Download as CSV file: xf-goe401-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3121 0.09548 0.09059 -0.0234 1.0000 0.0523
-7.500 -0.3200 0.09443 0.08965 -0.0247 1.0000 0.0532
-7.250 -0.3212 0.09292 0.08821 -0.0288 1.0000 0.0536
-7.000 -0.3178 0.09072 0.08607 -0.0327 1.0000 0.0539
-6.750 -0.3114 0.08557 0.08098 -0.0256 1.0000 0.0553
-6.500 -0.3070 0.08294 0.07842 -0.0242 1.0000 0.0566
-6.250 -0.3043 0.08066 0.07620 -0.0238 1.0000 0.0581
-6.000 -0.3032 0.07853 0.07413 -0.0237 1.0000 0.0595
-5.750 -0.2943 0.07604 0.07165 -0.0259 0.9979 0.0616
-5.500 -0.2299 0.07278 0.06798 -0.0465 0.9828 0.0649
-5.250 -0.2147 0.06678 0.06210 -0.0461 0.9748 0.0661
-5.000 -0.1924 0.06313 0.05848 -0.0470 0.9637 0.0686
-4.750 -0.1610 0.05976 0.05502 -0.0516 0.9510 0.0727
-4.500 -0.1029 0.05795 0.05266 -0.0634 0.9375 0.0780
-4.250 -0.0757 0.05318 0.04784 -0.0665 0.9272 0.0788
-4.000 -0.0484 0.04899 0.04365 -0.0688 0.9189 0.0800
-3.750 -0.0194 0.04594 0.04056 -0.0709 0.9084 0.0823
-3.500 0.0139 0.04344 0.03792 -0.0738 0.8971 0.0876
-3.250 0.0638 0.04254 0.03634 -0.0789 0.8855 0.0932
-2.750 0.1275 0.03198 0.02514 -0.0824 0.8621 0.0530
-2.500 0.1571 0.02988 0.02283 -0.0832 0.8484 0.0522
-2.250 0.1874 0.02778 0.02040 -0.0838 0.8344 0.0522
-2.000 0.2174 0.02579 0.01799 -0.0840 0.8202 0.0531
-1.750 0.2459 0.02413 0.01601 -0.0839 0.8053 0.0528
-1.500 0.2739 0.02265 0.01422 -0.0837 0.7900 0.0524
-1.250 0.3017 0.02130 0.01256 -0.0833 0.7743 0.0522
-1.000 0.3294 0.02013 0.01107 -0.0828 0.7578 0.0522
-0.750 0.3569 0.01913 0.00977 -0.0823 0.7409 0.0525
-0.500 0.3840 0.01829 0.00869 -0.0816 0.7232 0.0529
-0.250 0.4108 0.01764 0.00781 -0.0809 0.7048 0.0539
0.000 0.4367 0.01719 0.00731 -0.0803 0.6856 0.0565
0.250 0.4622 0.01685 0.00689 -0.0795 0.6650 0.0594
0.500 0.4878 0.01645 0.00637 -0.0787 0.6443 0.0613
0.750 0.5131 0.01613 0.00590 -0.0777 0.6239 0.0634
1.000 0.5385 0.01588 0.00556 -0.0769 0.6029 0.0663
1.250 0.5644 0.01577 0.00533 -0.0762 0.5825 0.0714
1.500 0.5902 0.01570 0.00514 -0.0755 0.5640 0.0812
1.750 0.6158 0.01567 0.00511 -0.0749 0.5467 0.1143
2.000 0.6414 0.01571 0.00514 -0.0743 0.5310 0.1705
2.500 0.7175 0.01441 0.00520 -0.0788 0.5008 1.0000
2.750 0.7421 0.01468 0.00532 -0.0780 0.4888 1.0000
3.000 0.7667 0.01496 0.00546 -0.0772 0.4778 1.0000
3.250 0.7912 0.01528 0.00561 -0.0764 0.4683 1.0000
3.500 0.8158 0.01557 0.00584 -0.0757 0.4582 1.0000
3.750 0.8404 0.01589 0.00606 -0.0750 0.4494 1.0000
4.000 0.8650 0.01622 0.00632 -0.0743 0.4406 1.0000
4.250 0.8895 0.01655 0.00661 -0.0736 0.4320 1.0000
4.500 0.9140 0.01691 0.00692 -0.0729 0.4240 1.0000
4.750 0.9383 0.01725 0.00727 -0.0722 0.4156 1.0000
5.000 0.9626 0.01762 0.00760 -0.0715 0.4079 1.0000
5.250 0.9868 0.01798 0.00803 -0.0708 0.3998 1.0000
5.500 1.0109 0.01836 0.00840 -0.0701 0.3923 1.0000
5.750 1.0347 0.01874 0.00885 -0.0694 0.3844 1.0000
6.000 1.0586 0.01913 0.00929 -0.0686 0.3772 1.0000
6.250 1.0819 0.01951 0.00976 -0.0678 0.3686 1.0000
6.500 1.1048 0.01988 0.01013 -0.0669 0.3599 1.0000
6.750 1.1269 0.02021 0.01060 -0.0659 0.3492 1.0000
7.000 1.1490 0.02057 0.01104 -0.0649 0.3396 1.0000
7.250 1.1710 0.02093 0.01149 -0.0639 0.3305 1.0000
7.500 1.1928 0.02132 0.01202 -0.0629 0.3210 1.0000
7.750 1.2142 0.02170 0.01247 -0.0618 0.3121 1.0000
8.000 1.2350 0.02209 0.01304 -0.0606 0.3017 1.0000
8.250 1.2557 0.02252 0.01361 -0.0595 0.2920 1.0000
8.500 1.2755 0.02295 0.01413 -0.0582 0.2820 1.0000
8.750 1.2936 0.02336 0.01466 -0.0566 0.2677 1.0000
9.000 1.3099 0.02382 0.01525 -0.0549 0.2480 1.0000
9.250 1.3228 0.02445 0.01585 -0.0528 0.2201 1.0000
9.500 1.3335 0.02535 0.01666 -0.0505 0.1858 1.0000
9.750 1.3407 0.02660 0.01775 -0.0479 0.1428 1.0000
10.000 1.3381 0.02860 0.01936 -0.0445 0.0938 1.0000
10.250 1.3336 0.03057 0.02117 -0.0407 0.0753 1.0000
10.500 1.3293 0.03248 0.02307 -0.0371 0.0660 1.0000
10.750 1.3256 0.03443 0.02515 -0.0340 0.0589 1.0000
11.000 1.3186 0.03676 0.02757 -0.0313 0.0538 1.0000
11.250 1.3114 0.03933 0.03026 -0.0292 0.0496 1.0000
11.500 1.3057 0.04203 0.03314 -0.0278 0.0457 1.0000
11.750 1.2971 0.04528 0.03653 -0.0269 0.0432 1.0000
12.000 1.2846 0.04923 0.04058 -0.0267 0.0413 1.0000
12.250 1.2771 0.05293 0.04444 -0.0268 0.0395 1.0000
12.500 1.2702 0.05677 0.04845 -0.0272 0.0376 1.0000
12.750 1.2623 0.06092 0.05273 -0.0279 0.0358 1.0000
13.000 1.2546 0.06520 0.05712 -0.0290 0.0344 1.0000
13.250 1.2458 0.06973 0.06173 -0.0302 0.0332 1.0000
13.500 1.2398 0.07381 0.06591 -0.0310 0.0321 1.0000
13.750 1.2371 0.07749 0.06974 -0.0316 0.0306 1.0000
14.000 1.2352 0.08101 0.07337 -0.0321 0.0295 1.0000
14.250 1.2340 0.08446 0.07694 -0.0326 0.0284 1.0000
14.500 1.2334 0.08788 0.08044 -0.0332 0.0275 1.0000
14.750 1.2334 0.09124 0.08385 -0.0338 0.0268 1.0000
15.000 1.2343 0.09433 0.08695 -0.0341 0.0259 1.0000
15.250 1.2353 0.09777 0.09059 -0.0346 0.0249 1.0000
15.500 1.2344 0.10160 0.09460 -0.0356 0.0240 1.0000
15.750 1.2325 0.10571 0.09887 -0.0369 0.0232 1.0000
16.000 1.2303 0.10991 0.10322 -0.0383 0.0226 1.0000
16.250 1.2274 0.11431 0.10776 -0.0399 0.0220 1.0000
16.500 1.2240 0.11889 0.11247 -0.0417 0.0217 1.0000
16.750 1.2200 0.12370 0.11744 -0.0438 0.0213 1.0000
17.000 1.2145 0.12891 0.12281 -0.0463 0.0211 1.0000
17.250 1.2081 0.13445 0.12849 -0.0491 0.0209 1.0000
17.500 1.1995 0.14068 0.13488 -0.0525 0.0208 1.0000
17.750 1.1884 0.14780 0.14217 -0.0567 0.0207 1.0000
18.000 1.1701 0.15731 0.15191 -0.0626 0.0209 1.0000
18.250 1.1243 0.17658 0.17147 -0.0749 0.0217 1.0000
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