GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 100,000 Max Cl/Cd: 50.38 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe318-il-100000.txt Download as CSV file: xf-goe318-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4210 0.10687 0.10263 0.0067 1.0000 0.0699
-8.250 -0.4191 0.10436 0.10021 0.0015 1.0000 0.0723
-8.000 -0.4207 0.10253 0.09850 -0.0092 1.0000 0.0733
-7.750 -0.4112 0.09756 0.09357 -0.0153 1.0000 0.0741
-7.500 -0.3948 0.09239 0.08845 -0.0067 1.0000 0.0768
-7.250 -0.3806 0.08885 0.08496 -0.0090 1.0000 0.0807
-7.000 -0.3649 0.08533 0.08147 -0.0196 1.0000 0.0861
-6.750 -0.3494 0.08118 0.07727 -0.0331 1.0000 0.0884
-6.500 -0.3335 0.07672 0.07290 -0.0297 0.9862 0.0909
-6.250 -0.3033 0.07244 0.06855 -0.0350 0.9653 0.0966
-6.000 -0.2678 0.06738 0.06320 -0.0490 0.9450 0.1038
-5.750 -0.2513 0.06403 0.05990 -0.0471 0.9300 0.1079
-5.500 -0.2239 0.06086 0.05636 -0.0552 0.9140 0.1188
-5.250 -0.2116 0.05770 0.05329 -0.0527 0.9013 0.1225
-5.000 -0.1856 0.05511 0.05034 -0.0578 0.8888 0.1342
-4.750 -0.1720 0.05210 0.04740 -0.0558 0.8785 0.1383
-4.500 -0.1484 0.04951 0.04456 -0.0582 0.8677 0.1508
-4.250 -0.1258 0.04733 0.04218 -0.0596 0.8577 0.1653
-4.000 -0.1063 0.04512 0.03985 -0.0595 0.8491 0.1808
-3.750 -0.0848 0.04277 0.03744 -0.0597 0.8395 0.1970
-3.500 -0.0640 0.04062 0.03521 -0.0595 0.8312 0.2141
-3.250 -0.0417 0.03890 0.03334 -0.0597 0.8226 0.2428
-2.250 0.0977 0.02994 0.02205 -0.0635 0.7914 0.1326
-2.000 0.1277 0.02740 0.01923 -0.0636 0.7832 0.1147
-1.750 0.1558 0.02577 0.01722 -0.0628 0.7760 0.1068
-1.500 0.1855 0.02483 0.01590 -0.0627 0.7674 0.1044
-1.250 0.2116 0.02394 0.01482 -0.0617 0.7601 0.1056
-1.000 0.2402 0.02319 0.01390 -0.0615 0.7501 0.1047
-0.750 0.2662 0.02245 0.01303 -0.0604 0.7413 0.1050
-0.500 0.2920 0.02174 0.01226 -0.0593 0.7308 0.1066
-0.250 0.3178 0.02115 0.01166 -0.0583 0.7190 0.1096
0.000 0.3430 0.02068 0.01112 -0.0570 0.7080 0.1162
0.250 0.3673 0.02006 0.01053 -0.0555 0.6987 0.1251
0.500 0.3942 0.01972 0.01020 -0.0550 0.6879 0.1375
0.750 0.4210 0.01918 0.00979 -0.0543 0.6799 0.1845
1.000 0.4510 0.01701 0.00939 -0.0537 0.6703 1.0000
1.250 0.4778 0.01720 0.00937 -0.0532 0.6604 1.0000
1.500 0.5037 0.01726 0.00921 -0.0522 0.6523 1.0000
1.750 0.5307 0.01748 0.00934 -0.0520 0.6411 1.0000
2.000 0.5572 0.01762 0.00936 -0.0515 0.6316 1.0000
2.250 0.5836 0.01768 0.00928 -0.0507 0.6222 1.0000
2.500 0.6104 0.01786 0.00940 -0.0504 0.6104 1.0000
2.750 0.6369 0.01795 0.00942 -0.0498 0.5993 1.0000
3.000 0.6632 0.01790 0.00922 -0.0488 0.5900 1.0000
3.250 0.6900 0.01799 0.00928 -0.0484 0.5766 1.0000
3.500 0.7167 0.01806 0.00931 -0.0480 0.5631 1.0000
3.750 0.7433 0.01812 0.00933 -0.0474 0.5494 1.0000
4.000 0.7700 0.01817 0.00933 -0.0469 0.5354 1.0000
4.250 0.7967 0.01822 0.00934 -0.0464 0.5208 1.0000
4.500 0.8234 0.01831 0.00939 -0.0459 0.5057 1.0000
4.750 0.8501 0.01846 0.00948 -0.0455 0.4906 1.0000
5.000 0.8767 0.01870 0.00965 -0.0451 0.4759 1.0000
5.250 0.9033 0.01903 0.00994 -0.0448 0.4621 1.0000
5.500 0.9299 0.01943 0.01031 -0.0445 0.4498 1.0000
5.750 0.9566 0.01982 0.01060 -0.0442 0.4396 1.0000
6.000 0.9829 0.02039 0.01123 -0.0442 0.4286 1.0000
6.250 1.0092 0.02104 0.01196 -0.0441 0.4199 1.0000
6.500 1.0358 0.02163 0.01257 -0.0440 0.4129 1.0000
6.750 1.0618 0.02242 0.01347 -0.0441 0.4064 1.0000
7.000 1.0878 0.02319 0.01440 -0.0441 0.4004 1.0000
7.250 1.1148 0.02388 0.01508 -0.0440 0.3962 1.0000
7.500 1.1392 0.02497 0.01646 -0.0441 0.3909 1.0000
7.750 1.1645 0.02581 0.01746 -0.0441 0.3855 1.0000
8.000 1.1913 0.02638 0.01806 -0.0439 0.3804 1.0000
8.250 1.2138 0.02724 0.01923 -0.0437 0.3719 1.0000
8.500 1.2383 0.02731 0.01935 -0.0431 0.3599 1.0000
8.750 1.2621 0.02676 0.01876 -0.0421 0.3417 1.0000
9.000 1.2856 0.02623 0.01809 -0.0411 0.3223 1.0000
9.250 1.3065 0.02632 0.01831 -0.0403 0.3057 1.0000
9.500 1.3253 0.02649 0.01873 -0.0394 0.2872 1.0000
9.750 1.3411 0.02662 0.01896 -0.0382 0.2616 1.0000
10.250 1.3255 0.03176 0.02342 -0.0345 0.1025 1.0000
10.500 1.3109 0.03533 0.02688 -0.0324 0.0876 1.0000
10.750 1.3016 0.03884 0.03045 -0.0318 0.0785 1.0000
11.000 1.2927 0.04255 0.03423 -0.0316 0.0730 1.0000
11.250 1.2860 0.04615 0.03791 -0.0316 0.0688 1.0000
11.500 1.2776 0.04991 0.04168 -0.0315 0.0659 1.0000
11.750 1.2752 0.05294 0.04475 -0.0307 0.0630 1.0000
12.000 1.2772 0.05550 0.04740 -0.0298 0.0598 1.0000
12.250 1.2811 0.05777 0.04962 -0.0286 0.0566 1.0000
12.500 1.2985 0.05861 0.05029 -0.0252 0.0529 1.0000
12.750 1.3146 0.06013 0.05199 -0.0232 0.0509 1.0000
13.000 1.3321 0.06188 0.05387 -0.0213 0.0492 1.0000
13.250 1.3455 0.06418 0.05631 -0.0199 0.0477 1.0000
13.500 1.3567 0.06675 0.05897 -0.0188 0.0460 1.0000
13.750 1.3841 0.07047 0.06266 -0.0165 0.0437 1.0000
14.000 1.3764 0.07430 0.06677 -0.0166 0.0436 1.0000
14.250 1.3685 0.07854 0.07129 -0.0169 0.0435 1.0000
14.500 1.3581 0.08316 0.07619 -0.0175 0.0435 1.0000
14.750 1.3456 0.08814 0.08143 -0.0185 0.0435 1.0000
15.000 1.3317 0.09350 0.08702 -0.0199 0.0436 1.0000
15.250 1.3172 0.09923 0.09297 -0.0216 0.0438 1.0000
15.500 1.2984 0.10467 0.09866 -0.0244 0.0440 1.0000
15.750 1.2761 0.11076 0.10500 -0.0281 0.0443 1.0000
16.000 1.2484 0.11847 0.11297 -0.0335 0.0448 1.0000
16.250 1.2026 0.13125 0.12612 -0.0434 0.0461 1.0000
16.500 1.0653 0.17711 0.17227 -0.0755 0.0572 1.0000
16.750 1.0776 0.17757 0.17277 -0.0749 0.0555 1.0000
17.000 1.0844 0.18017 0.17538 -0.0754 0.0544 1.0000
17.250 0.7743 0.17978 0.17514 -0.0559 0.0751 1.0000
17.500 0.7385 0.19533 0.19065 -0.0638 0.1247 1.0000
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Polar data table (+)
Polar graphs
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