GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 100,000 Max Cl/Cd: 36.02 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe14k-il-100000.txt Download as CSV file: xf-goe14k-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5559 0.10934 0.10472 -0.0244 1.0000 0.1301
-8.750 -0.5653 0.10651 0.10194 -0.0236 1.0000 0.1338
-8.500 -0.6005 0.10305 0.09858 -0.0252 1.0000 0.1374
-8.250 -0.6399 0.10012 0.09571 -0.0244 1.0000 0.1380
-8.000 -0.6836 0.09803 0.09364 -0.0205 1.0000 0.1385
-7.750 -0.7310 0.09550 0.09097 -0.0170 1.0000 0.1391
-7.500 -0.6675 0.09128 0.08694 -0.0151 1.0000 0.1455
-7.250 -0.6896 0.08842 0.08405 -0.0123 1.0000 0.1503
-7.000 -0.7528 0.08606 0.08137 -0.0085 1.0000 0.1541
-6.750 -0.7232 0.08141 0.07697 -0.0068 1.0000 0.1577
-6.500 -0.7234 0.07900 0.07453 -0.0038 1.0000 0.1642
-6.000 -0.7362 0.07310 0.06850 0.0024 1.0000 0.1792
-5.750 -0.7963 0.05507 0.04842 0.0118 1.0000 0.0955
-5.500 -0.7841 0.05196 0.04566 0.0129 1.0000 0.1000
-5.250 -0.7859 0.04680 0.03985 0.0187 1.0000 0.0890
-5.000 -0.7904 0.04289 0.03469 0.0267 1.0000 0.0820
-4.750 -0.7814 0.04047 0.03184 0.0305 1.0000 0.0819
-4.500 -0.7694 0.03768 0.02912 0.0326 1.0000 0.0861
-4.250 -0.7563 0.03597 0.02710 0.0355 1.0000 0.0881
-4.000 -0.7414 0.03412 0.02485 0.0385 1.0000 0.0901
-3.750 -0.7250 0.03272 0.02303 0.0412 1.0000 0.0932
-3.500 -0.7067 0.03119 0.02117 0.0431 1.0000 0.0980
-3.250 -0.6857 0.03004 0.01993 0.0443 1.0000 0.1026
-3.000 -0.6644 0.02921 0.01886 0.0457 1.0000 0.1083
-2.750 -0.6404 0.02813 0.01777 0.0461 1.0000 0.1145
-2.500 -0.6182 0.02754 0.01706 0.0471 1.0000 0.1225
-2.250 -0.5940 0.02680 0.01636 0.0475 1.0000 0.1298
-2.000 -0.5716 0.02638 0.01587 0.0484 1.0000 0.1395
-1.750 -0.2133 0.02963 0.02276 -0.0209 1.0000 1.0000
-1.500 -0.1965 0.02983 0.02274 -0.0194 1.0000 1.0000
-1.250 -0.1795 0.03006 0.02277 -0.0178 1.0000 1.0000
-1.000 -0.1625 0.03031 0.02283 -0.0163 1.0000 1.0000
-0.750 -0.1453 0.03059 0.02296 -0.0148 1.0000 1.0000
-0.500 -0.1281 0.03090 0.02311 -0.0134 1.0000 1.0000
-0.250 -0.1109 0.03123 0.02332 -0.0120 1.0000 1.0000
0.000 -0.0936 0.03159 0.02355 -0.0106 1.0000 1.0000
0.250 -0.0763 0.03197 0.02384 -0.0093 1.0000 1.0000
0.500 -0.0591 0.03238 0.02417 -0.0080 1.0000 1.0000
0.750 -0.0418 0.03281 0.02452 -0.0067 1.0000 1.0000
1.000 -0.0246 0.03327 0.02490 -0.0055 1.0000 1.0000
1.250 -0.0074 0.03376 0.02534 -0.0043 1.0000 1.0000
1.500 0.0097 0.03428 0.02581 -0.0031 1.0000 1.0000
1.750 0.0268 0.03482 0.02631 -0.0020 1.0000 1.0000
2.000 0.0438 0.03540 0.02686 -0.0009 1.0000 1.0000
2.250 0.0607 0.03601 0.02744 0.0002 1.0000 1.0000
2.500 0.0847 0.03659 0.02803 -0.0004 0.9976 1.0000
2.750 0.1801 0.03738 0.02889 -0.0156 0.9597 1.0000
3.000 0.2207 0.03772 0.02927 -0.0189 0.9445 1.0000
3.250 0.2585 0.03807 0.02967 -0.0216 0.9311 1.0000
3.500 0.2933 0.03840 0.03006 -0.0236 0.9189 1.0000
3.750 0.3282 0.03873 0.03046 -0.0256 0.9073 1.0000
4.000 0.3727 0.03918 0.03100 -0.0292 0.8977 1.0000
4.250 0.4046 0.03925 0.03117 -0.0303 0.8849 1.0000
4.500 0.4461 0.03909 0.03114 -0.0328 0.8704 1.0000
4.750 0.4942 0.03812 0.03031 -0.0356 0.8492 1.0000
5.000 0.5457 0.03695 0.02933 -0.0387 0.8313 1.0000
5.250 0.6454 0.03293 0.02562 -0.0476 0.8099 1.0000
5.500 0.6791 0.03149 0.02437 -0.0470 0.7908 1.0000
5.750 0.7167 0.02978 0.02288 -0.0468 0.7718 1.0000
6.000 0.7658 0.02693 0.02032 -0.0474 0.7500 1.0000
6.500 0.8378 0.02326 0.01426 -0.0422 0.2782 1.0000
6.750 0.8367 0.02514 0.01532 -0.0373 0.1958 1.0000
7.000 0.8468 0.02645 0.01633 -0.0342 0.1639 1.0000
7.250 0.8616 0.02758 0.01729 -0.0320 0.1440 1.0000
7.500 0.8832 0.02889 0.01836 -0.0312 0.1261 1.0000
7.750 0.9121 0.03017 0.01955 -0.0315 0.1114 1.0000
8.000 0.9511 0.03183 0.02116 -0.0337 0.0974 1.0000
8.250 0.9859 0.03332 0.02282 -0.0349 0.0881 1.0000
8.500 1.0445 0.03620 0.02589 -0.0410 0.0789 1.0000
8.750 1.1123 0.04053 0.03033 -0.0498 0.0710 1.0000
9.000 1.1240 0.04224 0.03249 -0.0464 0.0692 1.0000
9.250 1.1387 0.04484 0.03556 -0.0438 0.0677 1.0000
9.500 1.1473 0.04763 0.03878 -0.0402 0.0666 1.0000
9.750 1.1497 0.05010 0.04161 -0.0357 0.0653 1.0000
10.000 1.1492 0.05251 0.04434 -0.0310 0.0641 1.0000
10.250 1.1433 0.05509 0.04724 -0.0254 0.0638 1.0000
10.500 1.1306 0.05776 0.05022 -0.0188 0.0637 1.0000
10.750 1.1122 0.06083 0.05363 -0.0116 0.0649 1.0000
11.000 1.0933 0.06394 0.05703 -0.0050 0.0660 1.0000
11.250 1.0740 0.06726 0.06060 0.0010 0.0673 1.0000
11.500 1.0563 0.07075 0.06429 0.0061 0.0685 1.0000
11.750 1.0490 0.07503 0.06868 0.0092 0.0700 1.0000
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Polar data table (+)
Polar graphs
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