GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 100,000 Max Cl/Cd: 43.33 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe627-il-100000.txt Download as CSV file: xf-goe627-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3595 0.10935 0.10472 -0.0301 1.0000 0.1452
-9.500 -0.3551 0.10723 0.10263 -0.0282 1.0000 0.1492
-9.250 -0.3726 0.10495 0.10043 -0.0279 1.0000 0.1544
-9.000 -0.4405 0.10267 0.09834 -0.0307 1.0000 0.1571
-8.750 -0.4091 0.09898 0.09466 -0.0266 1.0000 0.1604
-8.500 -0.3984 0.09711 0.09281 -0.0236 1.0000 0.1643
-8.250 -0.4142 0.09493 0.09071 -0.0222 1.0000 0.1689
-8.000 -0.4661 0.09254 0.08846 -0.0218 1.0000 0.1721
-7.750 -0.5409 0.09050 0.08646 -0.0198 1.0000 0.1735
-7.500 -0.5502 0.08663 0.08265 -0.0175 1.0000 0.1760
-7.250 -0.5252 0.08510 0.08121 -0.0139 1.0000 0.1794
-7.000 -0.5363 0.08305 0.07919 -0.0113 1.0000 0.1841
-6.750 -0.5776 0.07849 0.07450 -0.0129 0.9975 0.1931
-6.500 -0.5373 0.07607 0.07215 -0.0139 0.9918 0.2001
-6.250 -0.5195 0.07195 0.06794 -0.0180 0.9827 0.2144
-6.000 -0.5610 0.04703 0.04032 -0.0234 0.9703 0.1008
-5.750 -0.5353 0.04398 0.03691 -0.0236 0.9608 0.0963
-5.500 -0.5035 0.04073 0.03316 -0.0248 0.9537 0.0926
-5.250 -0.4776 0.03841 0.03037 -0.0245 0.9437 0.0916
-5.000 -0.4453 0.03678 0.02841 -0.0254 0.9349 0.0927
-4.750 -0.4094 0.03511 0.02639 -0.0266 0.9264 0.0931
-4.500 -0.3775 0.03378 0.02479 -0.0271 0.9168 0.0936
-4.250 -0.3349 0.03256 0.02334 -0.0293 0.9094 0.0955
-4.000 -0.3045 0.03172 0.02231 -0.0294 0.8988 0.0984
-3.750 -0.2573 0.03034 0.02095 -0.0326 0.8925 0.1016
-3.500 -0.2289 0.02951 0.02018 -0.0324 0.8812 0.1049
-3.250 -0.1798 0.02852 0.01918 -0.0356 0.8754 0.1113
-3.000 -0.1563 0.02775 0.01854 -0.0346 0.8630 0.1181
-2.750 -0.1195 0.02683 0.01772 -0.0356 0.8548 0.1310
-2.500 -0.0891 0.02579 0.01688 -0.0354 0.8449 0.1597
-2.250 -0.0796 0.02347 0.01637 -0.0318 0.8342 0.4610
-2.000 0.0001 0.02245 0.01682 -0.0378 0.8306 0.8501
-1.750 0.2335 0.02324 0.01718 -0.0696 0.8427 0.9554
-1.500 0.3464 0.02235 0.01603 -0.0843 0.8371 0.9748
-1.250 0.4443 0.02101 0.01449 -0.0969 0.8291 0.9899
-1.000 0.5205 0.01974 0.01305 -0.1059 0.8164 1.0000
-0.750 0.5543 0.01901 0.01219 -0.1069 0.7991 1.0000
-0.500 0.5871 0.01839 0.01142 -0.1077 0.7796 1.0000
-0.250 0.6199 0.01787 0.01072 -0.1085 0.7584 1.0000
0.000 0.6443 0.01760 0.01028 -0.1077 0.7341 1.0000
0.250 0.6680 0.01743 0.00990 -0.1068 0.7088 1.0000
0.500 0.6902 0.01736 0.00962 -0.1056 0.6831 1.0000
0.750 0.7084 0.01740 0.00946 -0.1037 0.6567 1.0000
1.000 0.7275 0.01750 0.00932 -0.1020 0.6318 1.0000
1.250 0.7422 0.01768 0.00933 -0.0995 0.6065 1.0000
1.500 0.7588 0.01788 0.00931 -0.0974 0.5835 1.0000
1.750 0.7753 0.01813 0.00934 -0.0952 0.5622 1.0000
2.000 0.7894 0.01840 0.00947 -0.0927 0.5416 1.0000
2.250 0.8042 0.01869 0.00960 -0.0903 0.5226 1.0000
2.500 0.8196 0.01900 0.00975 -0.0881 0.5054 1.0000
2.750 0.8360 0.01933 0.00992 -0.0860 0.4898 1.0000
3.250 0.8684 0.02005 0.01039 -0.0818 0.4620 1.0000
3.500 0.8851 0.02047 0.01073 -0.0798 0.4502 1.0000
3.750 0.9064 0.02092 0.01099 -0.0787 0.4398 1.0000
4.000 0.9208 0.02135 0.01142 -0.0763 0.4293 1.0000
4.250 0.9408 0.02184 0.01180 -0.0750 0.4204 1.0000
4.500 0.9569 0.02229 0.01224 -0.0729 0.4115 1.0000
4.750 0.9790 0.02283 0.01265 -0.0721 0.4040 1.0000
5.000 0.9933 0.02335 0.01323 -0.0697 0.3966 1.0000
5.250 1.0169 0.02389 0.01366 -0.0691 0.3903 1.0000
5.500 1.0330 0.02452 0.01433 -0.0671 0.3842 1.0000
5.750 1.0486 0.02507 0.01492 -0.0650 0.3779 1.0000
6.000 1.0742 0.02566 0.01538 -0.0648 0.3724 1.0000
6.250 1.0880 0.02635 0.01617 -0.0625 0.3672 1.0000
6.500 1.1023 0.02702 0.01693 -0.0602 0.3623 1.0000
6.750 1.1233 0.02766 0.01757 -0.0592 0.3577 1.0000
7.000 1.1501 0.02846 0.01826 -0.0593 0.3534 1.0000
7.250 1.1565 0.02923 0.01925 -0.0557 0.3489 1.0000
7.500 1.1698 0.02998 0.02009 -0.0534 0.3444 1.0000
7.750 1.1903 0.03068 0.02080 -0.0523 0.3402 1.0000
8.000 1.2188 0.03162 0.02165 -0.0529 0.3365 1.0000
8.250 1.2196 0.03259 0.02288 -0.0485 0.3328 1.0000
8.500 1.2280 0.03351 0.02395 -0.0455 0.3286 1.0000
8.750 1.2446 0.03430 0.02479 -0.0439 0.3246 1.0000
9.000 1.2772 0.03502 0.02537 -0.0450 0.3201 1.0000
9.250 1.2704 0.03614 0.02676 -0.0396 0.3161 1.0000
9.500 1.2740 0.03702 0.02777 -0.0359 0.3111 1.0000
9.750 1.2969 0.03744 0.02816 -0.0353 0.3060 1.0000
10.000 1.3168 0.03834 0.02905 -0.0345 0.3016 1.0000
10.250 1.3035 0.03973 0.03071 -0.0284 0.2980 1.0000
10.500 1.3041 0.04087 0.03199 -0.0247 0.2940 1.0000
10.750 1.3247 0.04152 0.03265 -0.0239 0.2898 1.0000
11.000 1.3555 0.04237 0.03344 -0.0248 0.2856 1.0000
11.250 1.3220 0.04425 0.03562 -0.0162 0.2829 1.0000
11.500 1.2937 0.04623 0.03781 -0.0091 0.2798 1.0000
11.750 1.2934 0.04748 0.03916 -0.0059 0.2757 1.0000
12.000 1.3742 0.04673 0.03817 -0.0130 0.2697 1.0000
12.250 1.3175 0.04966 0.04142 -0.0029 0.2678 1.0000
12.500 1.2422 0.05484 0.04691 0.0060 0.2658 1.0000
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Polar data table (+)
Polar graphs
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