GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 200,000 Max Cl/Cd: 68.25 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe436-il-200000.txt Download as CSV file: xf-goe436-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3683 0.09753 0.09393 -0.0405 1.0000 0.0662
-9.000 -0.3887 0.09488 0.09138 -0.0423 1.0000 0.0665
-8.750 -0.4153 0.09264 0.08924 -0.0421 1.0000 0.0666
-8.500 -0.3819 0.08747 0.08403 -0.0377 1.0000 0.0679
-8.250 -0.3776 0.08554 0.08214 -0.0349 1.0000 0.0687
-8.000 -0.3851 0.08390 0.08056 -0.0322 1.0000 0.0695
-7.750 -0.4037 0.08270 0.07944 -0.0287 1.0000 0.0700
-7.500 -0.4234 0.08130 0.07812 -0.0258 1.0000 0.0705
-7.250 -0.4368 0.07944 0.07631 -0.0240 1.0000 0.0714
-7.000 -0.4359 0.07615 0.07301 -0.0263 0.9981 0.0733
-6.750 -0.4146 0.06410 0.06054 -0.0477 0.9871 0.0796
-6.500 -0.3869 0.06143 0.05795 -0.0488 0.9839 0.0810
-6.250 -0.3601 0.05869 0.05518 -0.0511 0.9779 0.0832
-6.000 -0.3278 0.05161 0.04740 -0.0620 0.9702 0.0932
-5.750 -0.3036 0.04860 0.04453 -0.0628 0.9631 0.0948
-5.500 -0.2692 0.04607 0.04200 -0.0657 0.9584 0.0977
-5.250 -0.2420 0.04225 0.03756 -0.0694 0.9496 0.1085
-5.000 -0.2093 0.03955 0.03499 -0.0715 0.9448 0.1112
-4.750 -0.1691 0.03707 0.03202 -0.0757 0.9410 0.1242
-4.500 -0.1446 0.03456 0.02960 -0.0760 0.9319 0.1267
-4.250 -0.1082 0.02731 0.02122 -0.0778 0.9275 0.0952
-4.000 -0.0709 0.02423 0.01772 -0.0794 0.9234 0.0870
-3.750 -0.0426 0.02236 0.01554 -0.0793 0.9152 0.0863
-3.500 -0.0035 0.02082 0.01373 -0.0811 0.9112 0.0878
-3.250 0.0259 0.01964 0.01233 -0.0810 0.9029 0.0888
-3.000 0.0617 0.01849 0.01098 -0.0821 0.8968 0.0901
-2.750 0.0932 0.01780 0.01012 -0.0822 0.8885 0.0918
-2.500 0.1259 0.01644 0.00869 -0.0829 0.8806 0.0948
-2.250 0.1548 0.01572 0.00796 -0.0827 0.8702 0.0975
-2.000 0.1887 0.01503 0.00722 -0.0834 0.8622 0.1006
-1.750 0.2153 0.01458 0.00672 -0.0826 0.8493 0.1042
-1.500 0.2429 0.01413 0.00622 -0.0821 0.8367 0.1078
-1.250 0.2697 0.01350 0.00564 -0.0815 0.8238 0.1126
-1.000 0.2969 0.01313 0.00525 -0.0809 0.8105 0.1179
-0.750 0.3233 0.01278 0.00487 -0.0802 0.7965 0.1249
-0.500 0.3482 0.01246 0.00458 -0.0792 0.7807 0.1347
-0.250 0.3720 0.01214 0.00429 -0.0780 0.7630 0.1483
0.000 0.3949 0.01171 0.00402 -0.0768 0.7436 0.1897
0.250 0.4998 0.00948 0.00395 -0.0918 0.7186 1.0000
0.500 0.5207 0.00954 0.00382 -0.0901 0.6931 1.0000
0.750 0.5418 0.00966 0.00371 -0.0885 0.6664 1.0000
1.000 0.5625 0.00985 0.00366 -0.0868 0.6386 1.0000
1.250 0.5829 0.01008 0.00367 -0.0850 0.6104 1.0000
1.500 0.6034 0.01034 0.00373 -0.0834 0.5840 1.0000
1.750 0.6242 0.01060 0.00380 -0.0819 0.5601 1.0000
2.000 0.6453 0.01086 0.00389 -0.0804 0.5392 1.0000
2.250 0.6669 0.01110 0.00400 -0.0790 0.5207 1.0000
2.500 0.6887 0.01137 0.00412 -0.0778 0.5051 1.0000
2.750 0.7110 0.01165 0.00426 -0.0766 0.4920 1.0000
3.000 0.7338 0.01192 0.00444 -0.0755 0.4804 1.0000
3.250 0.7571 0.01220 0.00465 -0.0746 0.4704 1.0000
3.750 0.8043 0.01281 0.00511 -0.0728 0.4529 1.0000
4.000 0.8289 0.01319 0.00536 -0.0722 0.4458 1.0000
4.250 0.8526 0.01345 0.00566 -0.0713 0.4386 1.0000
4.500 0.8772 0.01379 0.00592 -0.0707 0.4318 1.0000
4.750 0.9006 0.01409 0.00623 -0.0698 0.4235 1.0000
5.000 0.9243 0.01442 0.00647 -0.0690 0.4148 1.0000
5.250 0.9460 0.01464 0.00672 -0.0678 0.4046 1.0000
5.500 0.9692 0.01496 0.00698 -0.0669 0.3957 1.0000
5.750 0.9920 0.01519 0.00727 -0.0659 0.3882 1.0000
6.000 1.0166 0.01555 0.00757 -0.0653 0.3823 1.0000
6.250 1.0394 0.01581 0.00793 -0.0644 0.3757 1.0000
6.500 1.0627 0.01608 0.00822 -0.0635 0.3691 1.0000
6.750 1.0863 0.01642 0.00857 -0.0628 0.3630 1.0000
7.000 1.1086 0.01667 0.00891 -0.0618 0.3561 1.0000
7.250 1.1323 0.01701 0.00920 -0.0611 0.3496 1.0000
7.500 1.1527 0.01720 0.00954 -0.0597 0.3419 1.0000
7.750 1.1750 0.01747 0.00982 -0.0587 0.3351 1.0000
8.000 1.1956 0.01772 0.01019 -0.0574 0.3274 1.0000
8.250 1.2165 0.01796 0.01046 -0.0562 0.3199 1.0000
8.500 1.2361 0.01820 0.01082 -0.0548 0.3114 1.0000
8.750 1.2557 0.01846 0.01110 -0.0534 0.3034 1.0000
9.000 1.2735 0.01866 0.01147 -0.0516 0.2933 1.0000
9.250 1.2909 0.01892 0.01178 -0.0498 0.2834 1.0000
9.500 1.3062 0.01918 0.01208 -0.0477 0.2716 1.0000
9.750 1.3200 0.01945 0.01242 -0.0453 0.2565 1.0000
10.000 1.3313 0.01977 0.01281 -0.0426 0.2358 1.0000
10.250 1.3375 0.02031 0.01329 -0.0391 0.2104 1.0000
10.500 1.3396 0.02123 0.01405 -0.0353 0.1788 1.0000
10.750 1.3385 0.02252 0.01515 -0.0315 0.1498 1.0000
11.000 1.3370 0.02399 0.01649 -0.0279 0.1277 1.0000
11.250 1.3370 0.02547 0.01791 -0.0248 0.1114 1.0000
11.500 1.3381 0.02697 0.01939 -0.0220 0.1002 1.0000
11.750 1.3381 0.02861 0.02101 -0.0195 0.0917 1.0000
12.000 1.3413 0.03015 0.02260 -0.0174 0.0846 1.0000
12.250 1.3404 0.03205 0.02452 -0.0154 0.0795 1.0000
12.500 1.3410 0.03398 0.02651 -0.0137 0.0747 1.0000
12.750 1.3344 0.03659 0.02912 -0.0120 0.0709 1.0000
13.000 1.3325 0.03899 0.03164 -0.0108 0.0670 1.0000
13.250 1.3268 0.04188 0.03458 -0.0098 0.0634 1.0000
13.500 1.3144 0.04553 0.03821 -0.0089 0.0602 1.0000
13.750 1.3120 0.04846 0.04131 -0.0085 0.0567 1.0000
14.000 1.3067 0.05173 0.04464 -0.0082 0.0538 1.0000
14.250 1.3001 0.05502 0.04784 -0.0073 0.0505 1.0000
14.500 1.2984 0.05820 0.05122 -0.0075 0.0480 1.0000
14.750 1.2970 0.06131 0.05441 -0.0077 0.0454 1.0000
15.000 1.2974 0.06406 0.05709 -0.0074 0.0430 1.0000
15.250 1.2983 0.06697 0.06012 -0.0073 0.0411 1.0000
15.500 1.2979 0.07022 0.06352 -0.0078 0.0393 1.0000
15.750 1.2989 0.07324 0.06663 -0.0083 0.0377 1.0000
16.000 1.3023 0.07590 0.06931 -0.0085 0.0364 1.0000
16.250 1.3109 0.07777 0.07114 -0.0076 0.0351 1.0000
16.500 1.3073 0.08171 0.07529 -0.0088 0.0342 1.0000
16.750 1.3041 0.08561 0.07938 -0.0100 0.0332 1.0000
17.000 1.3024 0.08934 0.08326 -0.0111 0.0323 1.0000
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