GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 601 AIRFOIL (goe601-il) Reynolds number: 100,000 Max Cl/Cd: 47.73 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe601-il-100000.txt Download as CSV file: xf-goe601-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 601 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6348 0.07618 0.07067 -0.0767 1.0000 0.0912
-11.750 -0.6579 0.07170 0.06617 -0.0763 1.0000 0.0905
-11.500 -0.6914 0.06785 0.06230 -0.0747 1.0000 0.0900
-11.250 -0.7271 0.06507 0.05949 -0.0711 1.0000 0.0894
-11.000 -0.7631 0.06326 0.05766 -0.0656 1.0000 0.0889
-10.750 -0.8005 0.06196 0.05633 -0.0588 1.0000 0.0884
-10.500 -0.8321 0.05996 0.05423 -0.0530 1.0000 0.0880
-10.250 -0.8593 0.05770 0.05180 -0.0477 1.0000 0.0878
-10.000 -0.8807 0.05525 0.04914 -0.0429 1.0000 0.0878
-9.750 -0.8965 0.05272 0.04635 -0.0385 1.0000 0.0880
-9.500 -0.9074 0.05018 0.04352 -0.0345 1.0000 0.0883
-9.250 -0.9137 0.04773 0.04072 -0.0308 1.0000 0.0887
-9.000 -0.9155 0.04538 0.03803 -0.0275 1.0000 0.0893
-8.750 -0.9148 0.04337 0.03562 -0.0243 1.0000 0.0904
-8.500 -0.9120 0.04174 0.03353 -0.0211 1.0000 0.0916
-8.250 -0.9001 0.03956 0.03136 -0.0196 1.0000 0.0937
-8.000 -0.8857 0.03823 0.02995 -0.0181 0.9996 0.0958
-7.750 -0.8568 0.03678 0.02827 -0.0193 0.9952 0.0987
-7.500 -0.8291 0.03549 0.02661 -0.0200 0.9903 0.1022
-7.250 -0.8010 0.03397 0.02494 -0.0209 0.9857 0.1066
-7.000 -0.7688 0.03295 0.02389 -0.0225 0.9816 0.1120
-6.750 -0.7450 0.03201 0.02266 -0.0221 0.9764 0.1174
-6.500 -0.7145 0.03065 0.02149 -0.0233 0.9719 0.1258
-6.250 -0.6862 0.02955 0.02041 -0.0240 0.9675 0.1379
-6.000 -0.6656 0.02847 0.01944 -0.0233 0.9623 0.1526
-5.750 -0.6387 0.02772 0.01882 -0.0237 0.9575 0.1744
-5.500 -0.6148 0.02722 0.01843 -0.0236 0.9522 0.1956
-5.250 -0.5944 0.02683 0.01815 -0.0229 0.9465 0.2151
-5.000 -0.5643 0.02665 0.01802 -0.0238 0.9418 0.2412
-4.750 -0.5439 0.02634 0.01790 -0.0230 0.9362 0.2684
-4.500 -0.5246 0.02600 0.01773 -0.0220 0.9304 0.3108
-4.250 -0.4988 0.02577 0.01793 -0.0220 0.9259 0.3707
-4.000 -0.4828 0.02584 0.01819 -0.0200 0.9198 0.4182
-3.750 -0.4619 0.02608 0.01846 -0.0188 0.9138 0.4569
-3.500 -0.4301 0.02644 0.01879 -0.0196 0.9094 0.4900
-3.250 -0.4150 0.02653 0.01888 -0.0175 0.9030 0.5128
-3.000 -0.3914 0.02668 0.01898 -0.0169 0.8973 0.5372
-2.750 -0.3570 0.02692 0.01929 -0.0181 0.8932 0.5621
-2.500 -0.3449 0.02702 0.01943 -0.0155 0.8868 0.5820
-2.250 -0.3207 0.02719 0.01961 -0.0149 0.8810 0.6061
-2.000 -0.2847 0.02745 0.01992 -0.0162 0.8769 0.6312
-1.750 -0.2764 0.02761 0.02013 -0.0130 0.8700 0.6504
-1.500 -0.2507 0.02779 0.02035 -0.0127 0.8644 0.6723
-1.250 -0.2132 0.02804 0.02061 -0.0143 0.8603 0.6983
-1.000 -0.2080 0.02824 0.02087 -0.0106 0.8529 0.7187
-0.750 -0.1795 0.02842 0.02113 -0.0107 0.8473 0.7431
-0.500 -0.1380 0.02859 0.02135 -0.0127 0.8426 0.7716
-0.250 -0.1252 0.02871 0.02158 -0.0102 0.8326 0.7971
0.000 -0.0666 0.02865 0.02159 -0.0147 0.8267 0.8325
0.250 -0.0382 0.02881 0.02185 -0.0148 0.8152 0.8680
0.500 0.0456 0.02867 0.02172 -0.0236 0.8097 0.9024
0.750 0.1051 0.02899 0.02204 -0.0297 0.7985 0.9282
1.000 0.1922 0.02878 0.02177 -0.0397 0.7941 0.9449
1.250 0.2821 0.02833 0.02126 -0.0501 0.7919 0.9569
1.500 0.3446 0.02869 0.02163 -0.0573 0.7821 0.9759
1.750 0.4403 0.02772 0.02064 -0.0688 0.7793 0.9859
2.000 0.5350 0.02636 0.01928 -0.0800 0.7773 0.9922
2.250 0.6245 0.02479 0.01771 -0.0904 0.7746 0.9978
2.500 0.6130 0.02500 0.01789 -0.0848 0.7608 1.0000
2.750 0.6699 0.02368 0.01656 -0.0891 0.7563 1.0000
3.000 0.6538 0.02393 0.01678 -0.0818 0.7419 1.0000
3.250 0.6593 0.02380 0.01663 -0.0776 0.7297 1.0000
3.500 0.7158 0.02251 0.01534 -0.0815 0.7226 1.0000
3.750 0.7208 0.02240 0.01522 -0.0771 0.7087 1.0000
4.000 0.7418 0.02190 0.01472 -0.0751 0.6955 1.0000
4.250 0.7747 0.02111 0.01392 -0.0749 0.6823 1.0000
4.500 0.8031 0.02043 0.01323 -0.0740 0.6667 1.0000
4.750 0.8226 0.01995 0.01274 -0.0717 0.6475 1.0000
5.000 0.8452 0.01942 0.01216 -0.0697 0.6250 1.0000
5.250 0.8656 0.01906 0.01169 -0.0675 0.5981 1.0000
5.500 0.8875 0.01885 0.01132 -0.0656 0.5682 1.0000
5.750 0.9047 0.01896 0.01122 -0.0632 0.5379 1.0000
6.000 0.9189 0.01928 0.01137 -0.0604 0.5107 1.0000
6.250 0.9383 0.01966 0.01155 -0.0586 0.4882 1.0000
6.500 0.9582 0.02013 0.01184 -0.0571 0.4692 1.0000
6.750 0.9775 0.02065 0.01223 -0.0556 0.4526 1.0000
7.000 0.9938 0.02117 0.01268 -0.0535 0.4375 1.0000
7.250 1.0091 0.02170 0.01315 -0.0513 0.4230 1.0000
7.500 1.0240 0.02223 0.01362 -0.0490 0.4090 1.0000
7.750 1.0407 0.02279 0.01411 -0.0471 0.3962 1.0000
8.000 1.0632 0.02339 0.01461 -0.0463 0.3847 1.0000
8.250 1.0772 0.02395 0.01521 -0.0440 0.3737 1.0000
8.500 1.0944 0.02457 0.01583 -0.0423 0.3634 1.0000
9.000 1.1266 0.02579 0.01708 -0.0385 0.3432 1.0000
9.250 1.1442 0.02640 0.01765 -0.0370 0.3327 1.0000
9.500 1.1523 0.02690 0.01816 -0.0337 0.3216 1.0000
9.750 1.1556 0.02742 0.01875 -0.0297 0.3115 1.0000
10.000 1.1690 0.02793 0.01918 -0.0274 0.3007 1.0000
10.250 1.1648 0.02842 0.01986 -0.0223 0.2918 1.0000
10.500 1.1696 0.02893 0.02037 -0.0188 0.2815 1.0000
10.750 1.1670 0.02947 0.02103 -0.0144 0.2712 1.0000
11.000 1.1637 0.03013 0.02181 -0.0102 0.2604 1.0000
11.250 1.1589 0.03086 0.02260 -0.0061 0.2483 1.0000
11.500 1.1501 0.03184 0.02368 -0.0019 0.2339 1.0000
11.750 1.1392 0.03320 0.02519 0.0019 0.2142 1.0000
12.000 1.1265 0.03504 0.02704 0.0053 0.1861 1.0000
12.250 1.1119 0.03758 0.02936 0.0083 0.1488 1.0000
12.500 1.0989 0.04047 0.03197 0.0107 0.1232 1.0000
12.750 1.0901 0.04327 0.03463 0.0127 0.1106 1.0000
13.000 1.0850 0.04592 0.03724 0.0143 0.1026 1.0000
13.250 1.0794 0.04867 0.03993 0.0156 0.0977 1.0000
13.500 1.0789 0.05108 0.04239 0.0167 0.0934 1.0000
13.750 1.0791 0.05348 0.04482 0.0177 0.0896 1.0000
14.000 1.0813 0.05570 0.04695 0.0187 0.0865 1.0000
14.250 1.0902 0.05742 0.04872 0.0197 0.0840 1.0000
14.500 1.1008 0.05902 0.05039 0.0206 0.0815 1.0000
14.750 1.1135 0.06048 0.05183 0.0215 0.0787 1.0000
15.000 1.1436 0.06080 0.05192 0.0226 0.0756 1.0000
15.250 1.1533 0.06274 0.05405 0.0233 0.0742 1.0000
15.500 1.1651 0.06469 0.05617 0.0239 0.0726 1.0000
15.750 1.1771 0.06670 0.05832 0.0245 0.0713 1.0000
16.000 1.1872 0.06891 0.06065 0.0250 0.0699 1.0000
16.250 1.2002 0.07096 0.06277 0.0255 0.0685 1.0000
16.500 1.2353 0.07268 0.06440 0.0258 0.0662 1.0000
16.750 1.2275 0.07614 0.06811 0.0261 0.0660 1.0000
17.000 1.2158 0.08010 0.07234 0.0262 0.0658 1.0000
17.250 1.2017 0.08445 0.07695 0.0258 0.0656 1.0000
17.500 1.1847 0.08932 0.08208 0.0250 0.0656 1.0000
17.750 1.1655 0.09469 0.08769 0.0237 0.0657 1.0000
18.000 1.1408 0.10094 0.09420 0.0215 0.0657 1.0000
18.250 1.1167 0.10765 0.10113 0.0187 0.0660 1.0000
18.500 1.0900 0.11521 0.10890 0.0151 0.0662 1.0000
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