GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 100,000 Max Cl/Cd: 60.9 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe437-il-100000-n5.txt Download as CSV file: xf-goe437-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3055 0.09691 0.09241 -0.0287 1.0000 0.0376
-7.250 -0.3129 0.09561 0.09122 -0.0277 1.0000 0.0378
-7.000 -0.3193 0.09419 0.08991 -0.0280 1.0000 0.0382
-6.750 -0.3222 0.09232 0.08812 -0.0289 1.0000 0.0383
-6.500 -0.3229 0.09029 0.08616 -0.0299 1.0000 0.0385
-6.250 -0.3223 0.08805 0.08397 -0.0310 1.0000 0.0386
-6.000 -0.2920 0.08316 0.07903 -0.0395 0.9939 0.0387
-5.750 -0.2578 0.07770 0.07348 -0.0479 0.9870 0.0388
-5.500 -0.2264 0.07243 0.06814 -0.0546 0.9795 0.0388
-5.000 -0.1841 0.06156 0.05723 -0.0586 0.9668 0.0262
-4.750 -0.1508 0.05655 0.05210 -0.0653 0.9574 0.0246
-4.500 -0.1134 0.05146 0.04683 -0.0725 0.9497 0.0248
-4.250 -0.0735 0.04638 0.04153 -0.0794 0.9428 0.0254
-4.000 -0.0355 0.04143 0.03631 -0.0849 0.9352 0.0254
-3.750 0.0049 0.03622 0.03072 -0.0900 0.9290 0.0250
-3.500 0.0417 0.03119 0.02520 -0.0933 0.9215 0.0249
-3.250 0.0794 0.02641 0.01971 -0.0960 0.9152 0.0254
-3.000 0.1131 0.02294 0.01539 -0.0970 0.9075 0.0283
-2.750 0.1473 0.02074 0.01272 -0.0982 0.9008 0.0314
-2.500 0.1784 0.01922 0.01081 -0.0985 0.8919 0.0359
-2.250 0.2131 0.01799 0.00936 -0.0995 0.8852 0.0459
-2.000 0.2426 0.01703 0.00826 -0.0996 0.8747 0.0606
-1.750 0.2736 0.01653 0.00764 -0.0999 0.8644 0.0806
-1.500 0.3054 0.01598 0.00698 -0.1003 0.8541 0.0987
-1.250 0.3368 0.01544 0.00631 -0.1006 0.8423 0.1201
-1.000 0.3676 0.01501 0.00581 -0.1009 0.8288 0.1464
-0.750 0.3972 0.01466 0.00541 -0.1009 0.8144 0.1713
-0.500 0.4270 0.01439 0.00507 -0.1010 0.7999 0.2032
-0.250 0.4566 0.01401 0.00478 -0.1012 0.7857 0.2571
0.000 0.4962 0.01217 0.00453 -0.1033 0.7723 1.0000
0.250 0.5240 0.01226 0.00434 -0.1029 0.7573 1.0000
0.500 0.5512 0.01236 0.00421 -0.1025 0.7419 1.0000
0.750 0.5779 0.01248 0.00414 -0.1020 0.7264 1.0000
1.000 0.6043 0.01262 0.00410 -0.1015 0.7103 1.0000
1.250 0.6304 0.01276 0.00411 -0.1010 0.6940 1.0000
1.500 0.6562 0.01292 0.00413 -0.1004 0.6774 1.0000
1.750 0.6818 0.01308 0.00417 -0.0998 0.6607 1.0000
2.000 0.7072 0.01325 0.00424 -0.0992 0.6435 1.0000
2.250 0.7324 0.01343 0.00436 -0.0986 0.6260 1.0000
2.500 0.7577 0.01362 0.00446 -0.0979 0.6088 1.0000
2.750 0.7829 0.01382 0.00458 -0.0973 0.5927 1.0000
3.000 0.8081 0.01406 0.00476 -0.0967 0.5775 1.0000
3.250 0.8333 0.01431 0.00495 -0.0961 0.5632 1.0000
3.500 0.8583 0.01460 0.00519 -0.0955 0.5492 1.0000
3.750 0.8833 0.01490 0.00547 -0.0949 0.5362 1.0000
4.000 0.9083 0.01523 0.00582 -0.0944 0.5240 1.0000
4.250 0.9333 0.01557 0.00618 -0.0938 0.5121 1.0000
4.500 0.9581 0.01593 0.00656 -0.0933 0.5007 1.0000
4.750 0.9829 0.01629 0.00703 -0.0927 0.4891 1.0000
5.000 1.0076 0.01666 0.00751 -0.0921 0.4778 1.0000
5.250 1.0322 0.01704 0.00801 -0.0915 0.4670 1.0000
5.500 1.0567 0.01744 0.00852 -0.0909 0.4567 1.0000
5.750 1.0798 0.01779 0.00902 -0.0900 0.4414 1.0000
6.000 1.0962 0.01800 0.00923 -0.0878 0.4002 1.0000
6.250 1.1120 0.01846 0.00956 -0.0857 0.3499 1.0000
6.500 1.1245 0.01940 0.01013 -0.0832 0.2721 1.0000
7.000 1.1273 0.02468 0.01367 -0.0763 0.0291 1.0000
7.250 1.1398 0.02614 0.01530 -0.0740 0.0247 1.0000
7.500 1.1533 0.02737 0.01679 -0.0719 0.0213 1.0000
7.750 1.1637 0.02878 0.01843 -0.0694 0.0197 1.0000
8.000 1.1698 0.03039 0.02033 -0.0665 0.0186 1.0000
8.250 1.1706 0.03212 0.02223 -0.0630 0.0178 1.0000
8.500 1.1668 0.03417 0.02442 -0.0591 0.0170 1.0000
8.750 1.1686 0.03606 0.02640 -0.0561 0.0163 1.0000
9.000 1.1761 0.03767 0.02816 -0.0539 0.0153 1.0000
9.250 1.1845 0.03960 0.03020 -0.0517 0.0147 1.0000
9.500 1.1980 0.04167 0.03237 -0.0500 0.0143 1.0000
9.750 1.2171 0.04395 0.03479 -0.0487 0.0139 1.0000
10.000 1.2384 0.04658 0.03763 -0.0477 0.0136 1.0000
10.250 1.2556 0.04941 0.04074 -0.0465 0.0134 1.0000
10.500 1.2654 0.05221 0.04383 -0.0449 0.0130 1.0000
10.750 1.2694 0.05505 0.04695 -0.0430 0.0124 1.0000
11.000 1.2691 0.05794 0.05011 -0.0412 0.0119 1.0000
11.250 1.2663 0.06111 0.05355 -0.0396 0.0116 1.0000
11.500 1.2608 0.06453 0.05724 -0.0383 0.0114 1.0000
11.750 1.2527 0.06824 0.06123 -0.0373 0.0113 1.0000
12.000 1.2419 0.07238 0.06565 -0.0368 0.0113 1.0000
12.250 1.2297 0.07681 0.07036 -0.0370 0.0114 1.0000
12.500 1.2160 0.08161 0.07542 -0.0377 0.0115 1.0000
12.750 1.2010 0.08684 0.08090 -0.0392 0.0116 1.0000
13.000 1.1851 0.09254 0.08683 -0.0414 0.0117 1.0000
13.250 1.1686 0.09873 0.09324 -0.0443 0.0118 1.0000
13.500 1.1518 0.10536 0.10007 -0.0479 0.0119 1.0000
13.750 1.1347 0.11255 0.10745 -0.0521 0.0119 1.0000
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Polar data table (+)
Polar graphs
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