GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 100,000 Max Cl/Cd: 62.67 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe372-il-100000.txt Download as CSV file: xf-goe372-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 372 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3461 0.09429 0.08961 -0.0281 1.0000 0.0737
-7.250 -0.3553 0.09337 0.08883 -0.0288 1.0000 0.0750
-7.000 -0.3607 0.09280 0.08836 -0.0337 1.0000 0.0759
-6.750 -0.3594 0.09145 0.08704 -0.0393 1.0000 0.0763
-6.500 -0.3579 0.08493 0.08062 -0.0301 1.0000 0.0780
-6.250 -0.3559 0.08204 0.07778 -0.0272 1.0000 0.0799
-6.000 -0.3562 0.07972 0.07551 -0.0261 1.0000 0.0821
-5.750 -0.3567 0.07750 0.07333 -0.0260 1.0000 0.0846
-5.500 -0.3522 0.07545 0.07128 -0.0301 1.0000 0.0886
-5.250 -0.3383 0.07235 0.06808 -0.0382 1.0000 0.0906
-5.000 -0.3414 0.06895 0.06478 -0.0327 1.0000 0.0921
-4.750 -0.3375 0.06639 0.06224 -0.0306 1.0000 0.0947
-4.500 -0.3037 0.06307 0.05860 -0.0420 1.0000 0.1044
-4.250 -0.3088 0.06003 0.05576 -0.0357 1.0000 0.1073
-4.000 -0.2775 0.05668 0.05208 -0.0430 1.0000 0.1186
-3.750 -0.2725 0.05367 0.04917 -0.0400 1.0000 0.1213
-3.500 -0.2440 0.05036 0.04561 -0.0447 1.0000 0.1332
-3.250 -0.2107 0.04690 0.04202 -0.0484 0.9961 0.1479
-3.000 -0.1746 0.04383 0.03885 -0.0521 0.9903 0.1668
-2.750 -0.1304 0.04053 0.03528 -0.0578 0.9845 0.1909
-2.500 -0.0950 0.03814 0.03275 -0.0608 0.9779 0.2211
-2.250 -0.0177 0.02917 0.02197 -0.0707 0.9758 0.1153
-2.000 0.0265 0.02636 0.01857 -0.0740 0.9710 0.1119
-1.750 0.0664 0.02497 0.01650 -0.0762 0.9637 0.1176
-1.500 0.1078 0.02344 0.01483 -0.0792 0.9575 0.1231
-1.250 0.1455 0.02237 0.01339 -0.0809 0.9494 0.1299
-1.000 0.1891 0.02136 0.01218 -0.0839 0.9432 0.1437
-0.750 0.2238 0.02073 0.01159 -0.0854 0.9337 0.1656
-0.500 0.2671 0.02009 0.01100 -0.0885 0.9271 0.1942
-0.250 0.3043 0.01954 0.01054 -0.0903 0.9176 0.2211
0.000 0.3408 0.01903 0.01016 -0.0919 0.9084 0.2564
0.250 0.3890 0.01789 0.00969 -0.0958 0.9028 0.3933
0.500 0.4438 0.01647 0.00922 -0.1007 0.8967 1.0000
0.750 0.4881 0.01636 0.00894 -0.1036 0.8888 1.0000
1.000 0.5226 0.01637 0.00886 -0.1046 0.8776 1.0000
1.250 0.5583 0.01635 0.00877 -0.1058 0.8671 1.0000
1.500 0.6003 0.01615 0.00855 -0.1079 0.8597 1.0000
1.750 0.6301 0.01621 0.00859 -0.1079 0.8474 1.0000
2.000 0.6596 0.01628 0.00867 -0.1078 0.8352 1.0000
2.250 0.6889 0.01635 0.00875 -0.1076 0.8230 1.0000
2.500 0.7180 0.01638 0.00884 -0.1073 0.8103 1.0000
2.750 0.7464 0.01638 0.00887 -0.1067 0.7970 1.0000
3.000 0.7739 0.01640 0.00893 -0.1059 0.7833 1.0000
3.250 0.8007 0.01644 0.00903 -0.1050 0.7695 1.0000
3.500 0.8293 0.01592 0.00849 -0.1032 0.7492 1.0000
3.750 0.8511 0.01535 0.00793 -0.1001 0.7168 1.0000
4.000 0.8735 0.01502 0.00760 -0.0976 0.6862 1.0000
4.250 0.8957 0.01483 0.00741 -0.0953 0.6542 1.0000
4.500 0.9164 0.01474 0.00732 -0.0928 0.6140 1.0000
4.750 0.9319 0.01487 0.00707 -0.0890 0.5347 1.0000
5.000 0.9440 0.01565 0.00732 -0.0853 0.4160 1.0000
5.250 0.9470 0.01789 0.00816 -0.0813 0.1979 1.0000
5.500 0.9536 0.02036 0.00958 -0.0783 0.0605 1.0000
5.750 0.9716 0.02150 0.01081 -0.0762 0.0535 1.0000
6.000 0.9894 0.02259 0.01209 -0.0742 0.0497 1.0000
6.250 1.0030 0.02405 0.01366 -0.0719 0.0454 1.0000
6.500 1.0144 0.02576 0.01544 -0.0692 0.0433 1.0000
6.750 1.0307 0.02729 0.01703 -0.0670 0.0428 1.0000
7.000 1.0516 0.02910 0.01889 -0.0655 0.0427 1.0000
7.250 1.0801 0.03145 0.02122 -0.0651 0.0430 1.0000
7.500 1.1145 0.03454 0.02435 -0.0654 0.0438 1.0000
7.750 1.1406 0.03568 0.02581 -0.0640 0.0456 1.0000
8.000 1.1685 0.03830 0.02897 -0.0625 0.0493 1.0000
8.250 1.1910 0.04167 0.03278 -0.0610 0.0513 1.0000
8.500 1.2096 0.04543 0.03693 -0.0593 0.0530 1.0000
8.750 1.2277 0.04891 0.04110 -0.0565 0.0601 1.0000
9.000 1.2379 0.05513 0.04817 -0.0530 0.0751 1.0000
9.500 1.1409 0.06290 0.05799 -0.0395 0.1139 1.0000
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Polar data table (+)
Polar graphs
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