GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 100,000 Max Cl/Cd: 59.83 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe437-il-100000.txt Download as CSV file: xf-goe437-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3353 0.10607 0.10132 -0.0297 1.0000 0.0573
-8.000 -0.3445 0.10527 0.10065 -0.0303 1.0000 0.0575
-7.750 -0.3477 0.10374 0.09921 -0.0323 1.0000 0.0577
-7.500 -0.3241 0.09506 0.09050 -0.0271 1.0000 0.0602
-7.250 -0.3213 0.09242 0.08790 -0.0257 1.0000 0.0626
-7.000 -0.3250 0.09045 0.08602 -0.0245 1.0000 0.0645
-6.750 -0.3278 0.08843 0.08409 -0.0245 1.0000 0.0672
-6.500 -0.3306 0.08673 0.08248 -0.0260 1.0000 0.0691
-6.250 -0.3309 0.08604 0.08183 -0.0330 1.0000 0.0705
-6.000 -0.3283 0.08294 0.07878 -0.0348 1.0000 0.0711
-5.750 -0.3308 0.07883 0.07477 -0.0271 1.0000 0.0730
-5.500 -0.3299 0.07640 0.07239 -0.0252 1.0000 0.0751
-5.250 -0.3280 0.07409 0.07012 -0.0250 1.0000 0.0780
-4.750 -0.3024 0.06874 0.06463 -0.0354 1.0000 0.0844
-4.500 -0.3035 0.06564 0.06162 -0.0313 1.0000 0.0860
-4.250 -0.2973 0.06315 0.05915 -0.0301 1.0000 0.0890
-4.000 -0.2613 0.06028 0.05592 -0.0398 1.0000 0.0976
-3.750 -0.2544 0.05651 0.05227 -0.0376 0.9987 0.0997
-3.500 -0.1994 0.05220 0.04760 -0.0478 0.9920 0.1119
-3.000 -0.1182 0.04458 0.03969 -0.0581 0.9779 0.1406
-2.750 -0.0756 0.04102 0.03598 -0.0629 0.9711 0.1564
-2.500 -0.0312 0.03843 0.03303 -0.0676 0.9624 0.1794
-2.250 0.0357 0.02955 0.02274 -0.0735 0.9593 0.0800
-2.000 0.0821 0.02662 0.01905 -0.0765 0.9525 0.0823
-1.750 0.1265 0.02393 0.01569 -0.0790 0.9447 0.0845
-1.500 0.1681 0.02256 0.01413 -0.0815 0.9348 0.0999
-1.250 0.2180 0.02121 0.01251 -0.0851 0.9270 0.1235
-1.000 0.2606 0.01994 0.01119 -0.0875 0.9162 0.1499
-0.750 0.3021 0.01875 0.01011 -0.0896 0.9052 0.1879
-0.500 0.3459 0.01756 0.00912 -0.0922 0.8958 0.2515
-0.250 0.4057 0.01474 0.00826 -0.0979 0.8899 1.0000
0.000 0.4455 0.01452 0.00762 -0.0993 0.8770 1.0000
0.250 0.4829 0.01430 0.00716 -0.1004 0.8635 1.0000
0.500 0.5185 0.01409 0.00676 -0.1011 0.8489 1.0000
0.750 0.5521 0.01392 0.00642 -0.1014 0.8336 1.0000
1.000 0.5842 0.01379 0.00614 -0.1014 0.8178 1.0000
1.250 0.6110 0.01384 0.00607 -0.1006 0.7983 1.0000
1.500 0.6391 0.01389 0.00599 -0.1000 0.7802 1.0000
1.750 0.6671 0.01397 0.00594 -0.0994 0.7628 1.0000
2.000 0.6923 0.01417 0.00603 -0.0985 0.7434 1.0000
2.250 0.7179 0.01438 0.00614 -0.0976 0.7251 1.0000
2.500 0.7439 0.01459 0.00625 -0.0968 0.7077 1.0000
2.750 0.7690 0.01484 0.00645 -0.0959 0.6902 1.0000
3.000 0.7934 0.01510 0.00668 -0.0950 0.6721 1.0000
3.250 0.8183 0.01536 0.00689 -0.0942 0.6551 1.0000
3.500 0.8435 0.01560 0.00709 -0.0934 0.6388 1.0000
3.750 0.8689 0.01587 0.00736 -0.0926 0.6232 1.0000
4.000 0.8940 0.01618 0.00765 -0.0919 0.6077 1.0000
4.250 0.9187 0.01654 0.00802 -0.0912 0.5923 1.0000
4.500 0.9437 0.01693 0.00843 -0.0905 0.5777 1.0000
4.750 0.9688 0.01738 0.00890 -0.0899 0.5640 1.0000
5.000 0.9940 0.01786 0.00946 -0.0892 0.5507 1.0000
5.250 1.0192 0.01838 0.01003 -0.0886 0.5379 1.0000
5.500 1.0439 0.01889 0.01062 -0.0879 0.5244 1.0000
5.750 1.0649 0.01910 0.01088 -0.0863 0.5014 1.0000
6.000 1.0838 0.01895 0.01067 -0.0839 0.4698 1.0000
6.250 1.1026 0.01896 0.01079 -0.0819 0.4432 1.0000
6.500 1.1191 0.01886 0.01080 -0.0794 0.4097 1.0000
6.750 1.1308 0.01890 0.01076 -0.0760 0.3492 1.0000
7.000 1.1361 0.02017 0.01129 -0.0722 0.2091 1.0000
7.250 1.1324 0.02347 0.01337 -0.0682 0.0703 1.0000
7.500 1.1435 0.02516 0.01506 -0.0656 0.0573 1.0000
7.750 1.1536 0.02675 0.01677 -0.0629 0.0507 1.0000
8.000 1.1624 0.02828 0.01851 -0.0601 0.0470 1.0000
8.250 1.1668 0.03003 0.02038 -0.0569 0.0450 1.0000
8.500 1.1696 0.03196 0.02236 -0.0534 0.0438 1.0000
8.750 1.1811 0.03411 0.02448 -0.0510 0.0430 1.0000
9.000 1.2088 0.03644 0.02685 -0.0505 0.0424 1.0000
9.250 1.2355 0.03874 0.02933 -0.0499 0.0408 1.0000
9.500 1.2619 0.04140 0.03222 -0.0494 0.0393 1.0000
9.750 1.2896 0.04496 0.03608 -0.0490 0.0400 1.0000
10.000 1.3106 0.04900 0.04053 -0.0480 0.0413 1.0000
10.250 1.3353 0.05582 0.04760 -0.0483 0.0433 1.0000
10.500 1.3379 0.05591 0.04832 -0.0438 0.0458 1.0000
10.750 1.3279 0.06009 0.05320 -0.0397 0.0493 1.0000
11.000 1.3502 0.06690 0.06019 -0.0397 0.0552 1.0000
11.250 1.3178 0.06860 0.06250 -0.0338 0.0570 1.0000
11.500 1.2890 0.07196 0.06623 -0.0299 0.0585 1.0000
11.750 1.2642 0.07626 0.07081 -0.0280 0.0601 1.0000
12.000 1.2422 0.08118 0.07596 -0.0276 0.0616 1.0000
12.500 1.2070 0.09240 0.08757 -0.0294 0.0676 1.0000
12.750 1.1819 0.09845 0.09377 -0.0321 0.0675 1.0000
13.000 1.1569 0.10533 0.10077 -0.0360 0.0673 1.0000
13.250 1.1336 0.11283 0.10835 -0.0406 0.0670 1.0000
13.500 1.1089 0.12140 0.11694 -0.0464 0.0668 1.0000
13.750 1.0821 0.13149 0.12706 -0.0536 0.0667 1.0000
14.000 1.0349 0.14861 0.14410 -0.0676 0.0634 1.0000
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