GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 50,000 Max Cl/Cd: 42.1 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe437-il-50000-n5.txt Download as CSV file: xf-goe437-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 437 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3107 0.10647 0.09996 -0.0295 1.0000 0.0767
-7.750 -0.3183 0.10553 0.09916 -0.0297 1.0000 0.0774
-7.500 -0.3265 0.10463 0.09842 -0.0303 1.0000 0.0779
-7.250 -0.3288 0.10305 0.09695 -0.0319 1.0000 0.0781
-7.000 -0.3137 0.09663 0.09054 -0.0266 1.0000 0.0822
-6.750 -0.3139 0.09431 0.08831 -0.0261 1.0000 0.0850
-6.500 -0.3156 0.09236 0.08647 -0.0264 1.0000 0.0875
-6.250 -0.3189 0.09123 0.08545 -0.0291 1.0000 0.0901
-6.000 -0.3177 0.08991 0.08419 -0.0333 1.0000 0.0909
-5.750 -0.3153 0.08632 0.08070 -0.0321 1.0000 0.0916
-5.500 -0.3135 0.08287 0.07731 -0.0292 1.0000 0.0929
-5.250 -0.3107 0.08005 0.07454 -0.0281 1.0000 0.0945
-5.000 -0.3065 0.07745 0.07199 -0.0281 1.0000 0.0960
-4.750 -0.3001 0.07476 0.06931 -0.0290 1.0000 0.0977
-4.500 -0.2909 0.07186 0.06641 -0.0306 1.0000 0.0985
-4.250 -0.2374 0.06354 0.05768 -0.0439 0.9942 0.0495
-4.000 -0.2024 0.05877 0.05278 -0.0494 0.9870 0.0467
-3.750 -0.1600 0.05379 0.04751 -0.0569 0.9792 0.0467
-3.500 -0.1163 0.04897 0.04234 -0.0637 0.9715 0.0477
-3.250 -0.0727 0.04433 0.03730 -0.0696 0.9647 0.0474
-3.000 -0.0303 0.04000 0.03248 -0.0745 0.9572 0.0472
-2.750 0.0128 0.03581 0.02760 -0.0786 0.9503 0.0488
-2.500 0.0520 0.03305 0.02437 -0.0817 0.9427 0.0549
-2.250 0.0905 0.03035 0.02103 -0.0839 0.9346 0.0594
-2.000 0.1314 0.02828 0.01841 -0.0863 0.9276 0.0704
-1.750 0.1668 0.02672 0.01639 -0.0875 0.9179 0.0838
-1.500 0.2036 0.02569 0.01500 -0.0890 0.9089 0.1083
-1.250 0.2447 0.02448 0.01336 -0.0909 0.9007 0.1290
-1.000 0.2805 0.02378 0.01247 -0.0922 0.8901 0.1604
-0.750 0.3184 0.02300 0.01163 -0.0939 0.8802 0.1984
-0.500 0.3579 0.02213 0.01081 -0.0960 0.8710 0.2536
-0.250 0.3905 0.02087 0.01039 -0.0970 0.8592 0.4158
0.000 0.4290 0.01959 0.00974 -0.0980 0.8466 1.0000
0.250 0.4628 0.01956 0.00931 -0.0986 0.8328 1.0000
0.500 0.4957 0.01953 0.00898 -0.0990 0.8186 1.0000
0.750 0.5277 0.01952 0.00872 -0.0992 0.8042 1.0000
1.000 0.5589 0.01953 0.00852 -0.0993 0.7894 1.0000
1.250 0.5893 0.01958 0.00838 -0.0993 0.7746 1.0000
1.500 0.6192 0.01965 0.00831 -0.0992 0.7597 1.0000
1.750 0.6476 0.01978 0.00831 -0.0989 0.7442 1.0000
2.000 0.6748 0.01997 0.00840 -0.0984 0.7281 1.0000
2.250 0.7016 0.02017 0.00853 -0.0979 0.7123 1.0000
2.500 0.7280 0.02041 0.00873 -0.0974 0.6964 1.0000
2.750 0.7540 0.02066 0.00894 -0.0968 0.6805 1.0000
3.000 0.7797 0.02093 0.00919 -0.0962 0.6651 1.0000
3.250 0.8052 0.02121 0.00951 -0.0955 0.6498 1.0000
3.500 0.8306 0.02151 0.00982 -0.0949 0.6347 1.0000
3.750 0.8559 0.02182 0.01016 -0.0942 0.6201 1.0000
4.000 0.8812 0.02215 0.01059 -0.0936 0.6059 1.0000
4.250 0.9066 0.02251 0.01100 -0.0930 0.5920 1.0000
4.500 0.9319 0.02289 0.01147 -0.0924 0.5786 1.0000
4.750 0.9573 0.02332 0.01200 -0.0918 0.5658 1.0000
5.000 0.9827 0.02378 0.01263 -0.0912 0.5531 1.0000
5.250 1.0083 0.02428 0.01327 -0.0907 0.5412 1.0000
5.500 1.0343 0.02480 0.01394 -0.0902 0.5297 1.0000
5.750 1.0587 0.02542 0.01478 -0.0896 0.5177 1.0000
6.000 1.0821 0.02611 0.01581 -0.0888 0.5057 1.0000
6.250 1.1056 0.02682 0.01682 -0.0880 0.4938 1.0000
6.500 1.1282 0.02745 0.01774 -0.0869 0.4799 1.0000
6.750 1.1383 0.02714 0.01742 -0.0828 0.4374 1.0000
7.000 1.1455 0.02721 0.01749 -0.0788 0.3921 1.0000
7.250 1.1511 0.02769 0.01785 -0.0748 0.3382 1.0000
7.500 1.1540 0.02883 0.01869 -0.0710 0.2524 1.0000
8.000 1.1350 0.03543 0.02335 -0.0635 0.0508 1.0000
8.250 1.1342 0.03783 0.02588 -0.0605 0.0435 1.0000
8.500 1.1342 0.04011 0.02833 -0.0578 0.0395 1.0000
8.750 1.1329 0.04253 0.03096 -0.0554 0.0373 1.0000
9.000 1.1293 0.04525 0.03388 -0.0534 0.0357 1.0000
9.250 1.1237 0.04831 0.03711 -0.0518 0.0345 1.0000
9.500 1.1188 0.05151 0.04046 -0.0506 0.0335 1.0000
9.750 1.1178 0.05448 0.04368 -0.0496 0.0322 1.0000
10.000 1.1173 0.05751 0.04692 -0.0488 0.0306 1.0000
10.250 1.1180 0.06052 0.05011 -0.0479 0.0291 1.0000
10.500 1.1217 0.06324 0.05299 -0.0468 0.0280 1.0000
10.750 1.1322 0.06540 0.05531 -0.0449 0.0271 1.0000
11.000 1.1676 0.06632 0.05635 -0.0411 0.0258 1.0000
11.250 1.1948 0.06898 0.05929 -0.0392 0.0248 1.0000
11.500 1.1988 0.07238 0.06309 -0.0384 0.0242 1.0000
11.750 1.1990 0.07616 0.06723 -0.0380 0.0238 1.0000
12.000 1.1946 0.08038 0.07179 -0.0380 0.0234 1.0000
12.250 1.1879 0.08490 0.07662 -0.0385 0.0232 1.0000
12.500 1.1787 0.08979 0.08180 -0.0396 0.0232 1.0000
12.750 1.1674 0.09509 0.08737 -0.0412 0.0232 1.0000
13.000 1.1551 0.10077 0.09328 -0.0435 0.0232 1.0000
13.250 1.1416 0.10687 0.09961 -0.0464 0.0233 1.0000
13.500 1.1279 0.11332 0.10626 -0.0498 0.0235 1.0000
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Polar data table (+)
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