GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 200,000 Max Cl/Cd: 77.87 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe426-il-200000-n5.txt Download as CSV file: xf-goe426-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1341 0.08841 0.08490 -0.0648 0.9398 0.0463
-9.750 -0.1264 0.08417 0.08063 -0.0679 0.9277 0.0483
-9.500 -0.1442 0.07723 0.07368 -0.0753 0.9135 0.0506
-9.000 -0.2042 0.08258 0.07894 -0.0719 0.9440 0.0497
-8.500 -0.2239 0.06043 0.05664 -0.0931 0.8993 0.0357
-8.250 -0.2304 0.05460 0.05067 -0.0991 0.8750 0.0354
-8.000 -0.2374 0.04936 0.04518 -0.1024 0.8531 0.0352
-7.750 -0.2414 0.04442 0.03991 -0.1042 0.8340 0.0352
-7.500 -0.2434 0.03925 0.03421 -0.1052 0.8166 0.0355
-7.250 -0.2349 0.03571 0.03020 -0.1052 0.8013 0.0358
-7.000 -0.2208 0.03298 0.02708 -0.1050 0.7876 0.0358
-6.750 -0.2041 0.03059 0.02428 -0.1047 0.7752 0.0358
-6.500 -0.1852 0.02856 0.02182 -0.1042 0.7637 0.0360
-6.250 -0.1646 0.02676 0.01968 -0.1038 0.7522 0.0361
-6.000 -0.1428 0.02512 0.01778 -0.1035 0.7412 0.0364
-5.750 -0.1197 0.02382 0.01624 -0.1032 0.7308 0.0367
-5.500 -0.0957 0.02279 0.01503 -0.1029 0.7201 0.0372
-5.250 -0.0709 0.02200 0.01410 -0.1026 0.7103 0.0379
-5.000 -0.0459 0.02121 0.01313 -0.1023 0.7009 0.0386
-4.750 -0.0205 0.02036 0.01208 -0.1020 0.6915 0.0392
-4.500 0.0051 0.01953 0.01103 -0.1016 0.6825 0.0395
-4.250 0.0310 0.01878 0.01012 -0.1013 0.6726 0.0399
-4.000 0.0570 0.01813 0.00929 -0.1009 0.6638 0.0404
-3.750 0.0833 0.01753 0.00858 -0.1006 0.6547 0.0409
-3.500 0.1096 0.01701 0.00794 -0.1003 0.6465 0.0415
-3.250 0.1359 0.01654 0.00737 -0.1000 0.6376 0.0420
-3.000 0.1623 0.01619 0.00691 -0.0996 0.6296 0.0427
-2.750 0.1879 0.01563 0.00637 -0.0993 0.6215 0.0440
-2.500 0.2140 0.01528 0.00598 -0.0991 0.6145 0.0453
-2.250 0.2404 0.01497 0.00564 -0.0988 0.6068 0.0465
-2.000 0.2667 0.01469 0.00529 -0.0985 0.6004 0.0476
-1.750 0.2933 0.01444 0.00501 -0.0983 0.5935 0.0489
-1.500 0.3200 0.01426 0.00474 -0.0981 0.5873 0.0502
-1.250 0.3467 0.01404 0.00447 -0.0979 0.5815 0.0520
-1.000 0.3736 0.01387 0.00427 -0.0978 0.5753 0.0550
-0.750 0.4006 0.01378 0.00409 -0.0976 0.5700 0.0594
-0.500 0.4276 0.01364 0.00396 -0.0974 0.5646 0.0668
-0.250 0.4545 0.01344 0.00388 -0.0973 0.5591 0.1013
0.000 0.4778 0.01249 0.00386 -0.0972 0.5543 0.3931
0.250 0.5017 0.01212 0.00399 -0.0966 0.5496 0.5462
0.500 0.5261 0.01196 0.00411 -0.0957 0.5445 0.6396
0.750 0.5495 0.01184 0.00421 -0.0945 0.5399 0.7200
1.000 0.5730 0.01177 0.00426 -0.0933 0.5359 0.7929
1.250 0.6042 0.01154 0.00431 -0.0933 0.5310 0.9082
1.500 0.6472 0.01160 0.00431 -0.0966 0.5258 1.0000
1.750 0.6740 0.01176 0.00435 -0.0964 0.5217 1.0000
2.000 0.7009 0.01192 0.00443 -0.0963 0.5176 1.0000
2.250 0.7276 0.01206 0.00453 -0.0962 0.5128 1.0000
2.500 0.7544 0.01221 0.00463 -0.0960 0.5084 1.0000
2.750 0.7812 0.01239 0.00473 -0.0959 0.5045 1.0000
3.000 0.8079 0.01257 0.00486 -0.0957 0.5003 1.0000
3.250 0.8344 0.01272 0.00501 -0.0956 0.4955 1.0000
3.500 0.8609 0.01289 0.00516 -0.0954 0.4910 1.0000
3.750 0.8876 0.01309 0.00529 -0.0952 0.4873 1.0000
4.000 0.9138 0.01327 0.00549 -0.0950 0.4827 1.0000
4.250 0.9399 0.01344 0.00568 -0.0948 0.4778 1.0000
4.500 0.9660 0.01363 0.00585 -0.0945 0.4733 1.0000
4.750 0.9923 0.01384 0.00603 -0.0943 0.4693 1.0000
5.000 1.0179 0.01403 0.00628 -0.0940 0.4644 1.0000
5.250 1.0435 0.01422 0.00650 -0.0937 0.4595 1.0000
5.500 1.0692 0.01444 0.00669 -0.0934 0.4551 1.0000
5.750 1.0944 0.01465 0.00696 -0.0930 0.4500 1.0000
6.000 1.1195 0.01486 0.00723 -0.0927 0.4449 1.0000
6.250 1.1446 0.01508 0.00747 -0.0923 0.4404 1.0000
6.500 1.1694 0.01532 0.00775 -0.0919 0.4356 1.0000
6.750 1.1936 0.01555 0.00806 -0.0914 0.4298 1.0000
7.000 1.2179 0.01579 0.00832 -0.0908 0.4248 1.0000
7.250 1.2417 0.01604 0.00864 -0.0903 0.4193 1.0000
7.500 1.2649 0.01629 0.00897 -0.0896 0.4129 1.0000
7.750 1.2877 0.01655 0.00922 -0.0889 0.4068 1.0000
8.000 1.3098 0.01682 0.00962 -0.0880 0.3995 1.0000
8.250 1.3312 0.01710 0.00990 -0.0871 0.3924 1.0000
8.500 1.3512 0.01739 0.01027 -0.0859 0.3827 1.0000
8.750 1.3694 0.01771 0.01061 -0.0844 0.3717 1.0000
9.000 1.3855 0.01808 0.01099 -0.0827 0.3593 1.0000
9.250 1.3996 0.01852 0.01141 -0.0806 0.3457 1.0000
9.500 1.4097 0.01902 0.01190 -0.0779 0.3296 1.0000
9.750 1.4176 0.01963 0.01248 -0.0749 0.3134 1.0000
10.000 1.4242 0.02035 0.01318 -0.0720 0.2959 1.0000
10.250 1.4290 0.02122 0.01403 -0.0690 0.2766 1.0000
10.500 1.4321 0.02228 0.01504 -0.0661 0.2570 1.0000
10.750 1.4335 0.02353 0.01625 -0.0632 0.2350 1.0000
11.000 1.4291 0.02525 0.01785 -0.0601 0.2083 1.0000
11.250 1.4198 0.02750 0.01996 -0.0571 0.1785 1.0000
11.500 1.4072 0.03027 0.02259 -0.0544 0.1505 1.0000
12.000 1.3858 0.03636 0.02853 -0.0508 0.1128 1.0000
12.250 1.3778 0.03947 0.03163 -0.0497 0.0977 1.0000
12.500 1.3708 0.04264 0.03481 -0.0488 0.0826 1.0000
12.750 1.3599 0.04635 0.03847 -0.0481 0.0669 1.0000
13.000 1.3503 0.05011 0.04219 -0.0477 0.0558 1.0000
13.250 1.3420 0.05388 0.04597 -0.0476 0.0470 1.0000
13.500 1.3356 0.05757 0.04969 -0.0476 0.0402 1.0000
13.750 1.3304 0.06122 0.05339 -0.0477 0.0350 1.0000
14.000 1.3259 0.06491 0.05713 -0.0480 0.0317 1.0000
14.250 1.3219 0.06860 0.06089 -0.0483 0.0290 1.0000
14.500 1.3179 0.07239 0.06474 -0.0488 0.0272 1.0000
14.750 1.3161 0.07597 0.06842 -0.0493 0.0258 1.0000
15.000 1.3131 0.07976 0.07231 -0.0500 0.0245 1.0000
15.250 1.3096 0.08371 0.07633 -0.0508 0.0234 1.0000
15.500 1.3053 0.08785 0.08055 -0.0517 0.0226 1.0000
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Polar data table (+)
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