GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 510 AIRFOIL (goe510-il) Reynolds number: 100,000 Max Cl/Cd: 48.09 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe510-il-100000-n5.txt Download as CSV file: xf-goe510-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 510 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1800 0.10022 0.09523 -0.0719 0.9482 0.0901
-8.000 -0.1877 0.09713 0.09215 -0.0763 0.9387 0.0904
-7.750 -0.1811 0.09314 0.08817 -0.0777 0.9318 0.0908
-7.500 -0.1515 0.08913 0.08416 -0.0777 0.9300 0.0918
-7.250 -0.1445 0.08641 0.08144 -0.0776 0.9215 0.0924
-7.000 -0.1305 0.08320 0.07821 -0.0793 0.9150 0.0934
-6.500 -0.1516 0.06941 0.06409 -0.0869 0.8897 0.0671
-6.250 -0.1329 0.06621 0.06086 -0.0882 0.8838 0.0664
-6.000 -0.1247 0.06331 0.05790 -0.0877 0.8736 0.0656
-5.750 -0.1070 0.05922 0.05368 -0.0898 0.8673 0.0646
-5.500 -0.1011 0.05571 0.05003 -0.0891 0.8561 0.0638
-5.250 -0.0821 0.05085 0.04493 -0.0912 0.8506 0.0631
-5.000 -0.0771 0.04702 0.04086 -0.0897 0.8392 0.0632
-4.750 -0.0592 0.04156 0.03494 -0.0908 0.8342 0.0641
-4.500 -0.0541 0.03828 0.03126 -0.0881 0.8234 0.0645
-4.250 -0.0314 0.03483 0.02731 -0.0881 0.8184 0.0645
-4.000 -0.0180 0.03266 0.02475 -0.0859 0.8089 0.0648
-3.750 0.0079 0.03047 0.02211 -0.0857 0.8029 0.0654
-3.500 0.0326 0.02887 0.02008 -0.0851 0.7957 0.0664
-3.250 0.0566 0.02760 0.01845 -0.0842 0.7873 0.0678
-3.000 0.0945 0.02613 0.01684 -0.0861 0.7828 0.0693
-2.750 0.1115 0.02540 0.01598 -0.0839 0.7713 0.0701
-2.500 0.1517 0.02422 0.01460 -0.0860 0.7658 0.0712
-2.250 0.1707 0.02362 0.01388 -0.0841 0.7540 0.0722
-2.000 0.2058 0.02279 0.01289 -0.0852 0.7461 0.0739
-1.750 0.2325 0.02223 0.01221 -0.0847 0.7355 0.0761
-1.500 0.2616 0.02172 0.01154 -0.0846 0.7252 0.0780
-1.250 0.2978 0.02095 0.01074 -0.0860 0.7157 0.0801
-1.000 0.3213 0.02054 0.01032 -0.0850 0.7033 0.0818
-0.750 0.3516 0.02013 0.00984 -0.0852 0.6919 0.0840
-0.500 0.3873 0.01970 0.00931 -0.0865 0.6812 0.0876
-0.250 0.4119 0.01946 0.00901 -0.0856 0.6682 0.0915
0.000 0.4391 0.01919 0.00872 -0.0853 0.6553 0.0965
0.250 0.4694 0.01898 0.00843 -0.0855 0.6428 0.1022
0.500 0.5016 0.01875 0.00821 -0.0861 0.6305 0.1131
0.750 0.5270 0.01860 0.00821 -0.0855 0.6170 0.1432
1.000 0.5514 0.01856 0.00833 -0.0848 0.6038 0.2111
1.250 0.5764 0.01866 0.00838 -0.0841 0.5912 0.2528
1.500 0.6009 0.01878 0.00842 -0.0833 0.5788 0.2843
1.750 0.6207 0.01888 0.00852 -0.0817 0.5660 0.3078
2.000 0.6425 0.01897 0.00856 -0.0805 0.5542 0.3304
2.250 0.6658 0.01903 0.00854 -0.0795 0.5435 0.3510
2.500 0.6831 0.01906 0.00860 -0.0775 0.5324 0.3737
2.750 0.7021 0.01902 0.00860 -0.0758 0.5227 0.4080
3.250 0.8996 0.01925 0.00973 -0.1051 0.4938 1.0000
3.500 0.9146 0.01950 0.00991 -0.1026 0.4851 1.0000
3.750 0.9322 0.01976 0.01002 -0.1007 0.4778 1.0000
4.000 0.9479 0.02003 0.01023 -0.0984 0.4704 1.0000
4.250 0.9645 0.02030 0.01040 -0.0963 0.4634 1.0000
4.500 0.9819 0.02060 0.01060 -0.0943 0.4569 1.0000
4.750 0.9971 0.02089 0.01086 -0.0920 0.4502 1.0000
5.000 1.0159 0.02120 0.01106 -0.0903 0.4443 1.0000
5.250 1.0316 0.02152 0.01135 -0.0881 0.4383 1.0000
5.500 1.0464 0.02184 0.01165 -0.0857 0.4322 1.0000
5.750 1.0662 0.02217 0.01189 -0.0843 0.4270 1.0000
6.000 1.0804 0.02252 0.01224 -0.0818 0.4214 1.0000
6.250 1.0939 0.02286 0.01259 -0.0793 0.4155 1.0000
6.500 1.1127 0.02322 0.01288 -0.0777 0.4105 1.0000
6.750 1.1297 0.02361 0.01326 -0.0759 0.4056 1.0000
7.000 1.1414 0.02399 0.01369 -0.0730 0.4000 1.0000
7.250 1.1576 0.02437 0.01406 -0.0711 0.3948 1.0000
7.500 1.1779 0.02478 0.01441 -0.0699 0.3901 1.0000
7.750 1.1865 0.02522 0.01496 -0.0666 0.3846 1.0000
8.000 1.2007 0.02566 0.01543 -0.0644 0.3796 1.0000
8.250 1.2195 0.02606 0.01580 -0.0630 0.3749 1.0000
8.500 1.2304 0.02657 0.01639 -0.0603 0.3698 1.0000
8.750 1.2406 0.02708 0.01698 -0.0575 0.3644 1.0000
9.000 1.2562 0.02754 0.01745 -0.0557 0.3597 1.0000
9.250 1.2721 0.02803 0.01797 -0.0540 0.3552 1.0000
9.500 1.2786 0.02868 0.01876 -0.0508 0.3498 1.0000
9.750 1.2904 0.02923 0.01936 -0.0485 0.3447 1.0000
10.000 1.3083 0.02967 0.01976 -0.0472 0.3403 1.0000
10.250 1.3110 0.03049 0.02075 -0.0437 0.3347 1.0000
10.500 1.3173 0.03115 0.02149 -0.0408 0.3285 1.0000
10.750 1.3262 0.03170 0.02203 -0.0383 0.3224 1.0000
11.000 1.3247 0.03269 0.02318 -0.0347 0.3150 1.0000
11.250 1.3309 0.03329 0.02371 -0.0321 0.3077 1.0000
11.500 1.3262 0.03459 0.02519 -0.0286 0.2993 1.0000
11.750 1.3298 0.03546 0.02602 -0.0260 0.2918 1.0000
12.000 1.3269 0.03698 0.02772 -0.0232 0.2838 1.0000
12.250 1.3293 0.03813 0.02884 -0.0209 0.2763 1.0000
12.500 1.3264 0.03990 0.03077 -0.0186 0.2684 1.0000
12.750 1.3274 0.04137 0.03225 -0.0166 0.2613 1.0000
13.000 1.3233 0.04347 0.03448 -0.0147 0.2531 1.0000
13.250 1.3220 0.04536 0.03639 -0.0130 0.2460 1.0000
13.500 1.3184 0.04772 0.03889 -0.0116 0.2391 1.0000
13.750 1.3152 0.05009 0.04133 -0.0104 0.2323 1.0000
14.000 1.3082 0.05299 0.04434 -0.0093 0.2245 1.0000
14.250 1.3004 0.05609 0.04749 -0.0085 0.2166 1.0000
14.500 1.2906 0.05966 0.05116 -0.0079 0.2089 1.0000
14.750 1.2807 0.06333 0.05489 -0.0076 0.2013 1.0000
15.000 1.2703 0.06731 0.05900 -0.0075 0.1948 1.0000
15.250 1.2581 0.07163 0.06340 -0.0077 0.1877 1.0000
15.500 1.2472 0.07593 0.06781 -0.0080 0.1817 1.0000
15.750 1.2338 0.08074 0.07273 -0.0087 0.1747 1.0000
16.000 1.2226 0.08531 0.07738 -0.0094 0.1683 1.0000
16.250 1.2082 0.09050 0.08266 -0.0104 0.1602 1.0000
16.500 1.1960 0.09541 0.08765 -0.0114 0.1529 1.0000
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Polar data table (+)
Polar graphs
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