GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 100,000 Max Cl/Cd: 53.88 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe401-il-100000.txt Download as CSV file: xf-goe401-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 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 -0.3104 0.09386 0.08902 -0.0215 1.0000 0.0694
-7.250 -0.3132 0.09207 0.08732 -0.0214 1.0000 0.0711
-7.000 -0.3148 0.09084 0.08618 -0.0239 1.0000 0.0729
-6.750 -0.3137 0.09152 0.08688 -0.0318 1.0000 0.0741
-6.500 -0.3099 0.08787 0.08329 -0.0327 1.0000 0.0748
-6.250 -0.3067 0.08254 0.07807 -0.0264 1.0000 0.0762
-6.000 -0.3036 0.07970 0.07530 -0.0241 1.0000 0.0778
-5.750 -0.3024 0.07750 0.07316 -0.0229 1.0000 0.0793
-5.500 -0.3031 0.07556 0.07128 -0.0218 1.0000 0.0811
-5.250 -0.3038 0.07377 0.06952 -0.0212 1.0000 0.0831
-5.000 -0.3008 0.07221 0.06796 -0.0220 1.0000 0.0859
-4.750 -0.2780 0.07318 0.06859 -0.0309 1.0000 0.0888
-4.500 -0.2808 0.06843 0.06399 -0.0275 1.0000 0.0896
-4.250 -0.2693 0.06451 0.06016 -0.0267 0.9973 0.0913
-4.000 -0.2326 0.06076 0.05636 -0.0316 0.9896 0.0972
-3.750 -0.1749 0.05725 0.05252 -0.0430 0.9806 0.1051
-3.500 -0.1422 0.05321 0.04849 -0.0461 0.9728 0.1091
-3.000 -0.0565 0.04679 0.04174 -0.0573 0.9536 0.1232
-2.750 -0.0041 0.04429 0.03890 -0.0640 0.9453 0.1354
-2.500 0.0313 0.04160 0.03617 -0.0667 0.9344 0.1466
-2.250 0.0710 0.03845 0.03293 -0.0704 0.9250 0.1557
-2.000 0.1186 0.03575 0.03004 -0.0750 0.9171 0.1705
-1.750 0.1634 0.03401 0.02800 -0.0787 0.9062 0.1935
-1.500 0.2051 0.03095 0.02494 -0.0820 0.8975 0.2124
-1.250 0.2441 0.02888 0.02272 -0.0844 0.8857 0.2531
-1.000 0.2773 0.02705 0.02081 -0.0853 0.8710 0.2963
-0.750 0.3098 0.02507 0.01875 -0.0859 0.8552 0.3294
-0.500 0.3780 0.02343 0.01565 -0.0879 0.8400 0.1161
-0.250 0.4135 0.02197 0.01361 -0.0874 0.8221 0.1034
0.000 0.4403 0.02068 0.01217 -0.0864 0.7996 0.1019
0.250 0.4693 0.01967 0.01092 -0.0855 0.7779 0.1014
0.500 0.4964 0.01892 0.00994 -0.0844 0.7549 0.1049
0.750 0.5226 0.01834 0.00929 -0.0834 0.7316 0.1104
1.000 0.5493 0.01781 0.00858 -0.0823 0.7095 0.1153
1.250 0.5748 0.01731 0.00803 -0.0811 0.6875 0.1233
1.500 0.6015 0.01692 0.00756 -0.0802 0.6680 0.1435
1.750 0.6282 0.01616 0.00690 -0.0795 0.6504 0.2401
2.000 0.6828 0.01460 0.00662 -0.0848 0.6288 1.0000
2.250 0.7074 0.01488 0.00667 -0.0838 0.6127 1.0000
2.500 0.7321 0.01518 0.00676 -0.0829 0.5978 1.0000
2.750 0.7569 0.01549 0.00689 -0.0820 0.5839 1.0000
3.000 0.7819 0.01582 0.00705 -0.0812 0.5711 1.0000
3.250 0.8067 0.01616 0.00727 -0.0804 0.5585 1.0000
3.500 0.8309 0.01653 0.00757 -0.0795 0.5459 1.0000
3.750 0.8552 0.01693 0.00790 -0.0787 0.5341 1.0000
4.000 0.8802 0.01734 0.00821 -0.0780 0.5232 1.0000
4.250 0.9052 0.01775 0.00855 -0.0773 0.5125 1.0000
4.500 0.9288 0.01821 0.00903 -0.0765 0.5012 1.0000
4.750 0.9532 0.01871 0.00950 -0.0757 0.4909 1.0000
5.000 0.9787 0.01920 0.00991 -0.0752 0.4813 1.0000
5.250 1.0015 0.01973 0.01053 -0.0742 0.4703 1.0000
5.500 1.0257 0.02032 0.01113 -0.0735 0.4609 1.0000
5.750 1.0504 0.02088 0.01167 -0.0729 0.4515 1.0000
6.000 1.0727 0.02153 0.01247 -0.0719 0.4414 1.0000
6.250 1.0975 0.02214 0.01304 -0.0713 0.4324 1.0000
6.500 1.1199 0.02268 0.01368 -0.0703 0.4216 1.0000
6.750 1.1415 0.02326 0.01435 -0.0692 0.4104 1.0000
7.000 1.1649 0.02373 0.01485 -0.0683 0.3997 1.0000
7.250 1.1877 0.02420 0.01539 -0.0673 0.3896 1.0000
7.500 1.2084 0.02483 0.01620 -0.0661 0.3797 1.0000
7.750 1.2323 0.02520 0.01658 -0.0653 0.3700 1.0000
8.000 1.2530 0.02554 0.01709 -0.0640 0.3591 1.0000
8.250 1.2729 0.02599 0.01773 -0.0626 0.3487 1.0000
8.500 1.2932 0.02599 0.01782 -0.0611 0.3357 1.0000
8.750 1.3105 0.02559 0.01751 -0.0590 0.3184 1.0000
9.000 1.3257 0.02511 0.01710 -0.0566 0.2988 1.0000
9.250 1.3388 0.02499 0.01715 -0.0540 0.2782 1.0000
9.500 1.3485 0.02503 0.01732 -0.0509 0.2487 1.0000
9.750 1.3490 0.02583 0.01796 -0.0468 0.1878 1.0000
10.000 1.3371 0.02832 0.01982 -0.0419 0.1199 1.0000
10.250 1.3254 0.03073 0.02196 -0.0370 0.0988 1.0000
10.500 1.3139 0.03306 0.02417 -0.0326 0.0891 1.0000
10.750 1.3074 0.03529 0.02648 -0.0291 0.0812 1.0000
11.000 1.2977 0.03796 0.02909 -0.0262 0.0761 1.0000
11.250 1.2962 0.04028 0.03154 -0.0241 0.0710 1.0000
11.500 1.2954 0.04284 0.03399 -0.0221 0.0667 1.0000
11.750 1.3077 0.04495 0.03611 -0.0203 0.0630 1.0000
12.000 1.3201 0.04702 0.03829 -0.0188 0.0596 1.0000
12.250 1.3604 0.05002 0.04101 -0.0187 0.0539 1.0000
12.500 1.3653 0.05231 0.04360 -0.0171 0.0527 1.0000
12.750 1.3733 0.05503 0.04663 -0.0157 0.0517 1.0000
13.000 1.3779 0.05805 0.04993 -0.0145 0.0508 1.0000
13.250 1.3775 0.06132 0.05348 -0.0133 0.0503 1.0000
13.500 1.3716 0.06482 0.05726 -0.0123 0.0497 1.0000
13.750 1.3622 0.06861 0.06132 -0.0117 0.0493 1.0000
14.000 1.3502 0.07272 0.06570 -0.0117 0.0491 1.0000
14.250 1.3345 0.07737 0.07060 -0.0122 0.0490 1.0000
14.500 1.3166 0.08244 0.07592 -0.0135 0.0487 1.0000
14.750 1.2956 0.08823 0.08197 -0.0156 0.0490 1.0000
15.000 1.2716 0.09491 0.08890 -0.0187 0.0496 1.0000
15.250 1.2454 0.10239 0.09662 -0.0227 0.0502 1.0000
15.500 1.2185 0.11063 0.10507 -0.0275 0.0509 1.0000
15.750 1.1917 0.11967 0.11428 -0.0330 0.0519 1.0000
16.000 1.1637 0.12968 0.12442 -0.0394 0.0526 1.0000
16.250 1.1427 0.13911 0.13391 -0.0447 0.0536 1.0000
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Polar data table (+)
Polar graphs
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