A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: A18 (smoothed) (a18sm-il) Reynolds number: 100,000 Max Cl/Cd: 65.27 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a18sm-il-100000.txt Download as CSV file: xf-a18sm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: A18 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3957 0.10254 0.09748 -0.0273 1.0000 0.0899
-8.000 -0.4126 0.10196 0.09705 -0.0287 1.0000 0.0914
-7.750 -0.4240 0.10071 0.09593 -0.0346 1.0000 0.0920
-7.500 -0.4117 0.09485 0.09007 -0.0285 1.0000 0.0936
-7.250 -0.4018 0.09153 0.08675 -0.0258 1.0000 0.0962
-7.000 -0.3995 0.08890 0.08418 -0.0255 1.0000 0.0992
-6.750 -0.4005 0.08636 0.08171 -0.0275 1.0000 0.1031
-6.500 -0.3989 0.08273 0.07812 -0.0408 1.0000 0.1063
-6.250 -0.3953 0.07935 0.07480 -0.0337 1.0000 0.1078
-6.000 -0.3891 0.07666 0.07214 -0.0311 1.0000 0.1106
-5.750 -0.3745 0.07308 0.06852 -0.0393 1.0000 0.1188
-5.500 -0.3641 0.06858 0.06401 -0.0420 1.0000 0.1215
-5.250 -0.3333 0.06448 0.05962 -0.0536 1.0000 0.1341
-5.000 -0.3355 0.06177 0.05714 -0.0455 1.0000 0.1362
-4.750 -0.3236 0.05943 0.05480 -0.0442 1.0000 0.1438
-4.500 -0.2302 0.03601 0.02972 -0.0755 1.0000 0.0799
-4.250 -0.1932 0.03090 0.02379 -0.0793 1.0000 0.0779
-4.000 -0.1697 0.02924 0.02219 -0.0797 1.0000 0.0847
-3.750 -0.1334 0.02577 0.01796 -0.0822 1.0000 0.0879
-3.500 -0.1011 0.02369 0.01538 -0.0835 1.0000 0.0957
-3.250 -0.0703 0.02246 0.01368 -0.0842 1.0000 0.1055
-3.000 -0.0413 0.02141 0.01253 -0.0847 1.0000 0.1182
-2.750 -0.0125 0.02062 0.01155 -0.0851 1.0000 0.1342
-2.500 0.0148 0.01999 0.01102 -0.0855 1.0000 0.1534
-2.250 0.0425 0.01955 0.01046 -0.0858 1.0000 0.1771
-2.000 0.0688 0.01925 0.01023 -0.0860 1.0000 0.2048
-1.750 0.0953 0.01900 0.01005 -0.0863 1.0000 0.2341
-1.500 0.1209 0.01884 0.01005 -0.0865 1.0000 0.2668
-1.250 0.1467 0.01879 0.01013 -0.0868 1.0000 0.3056
-1.000 0.1727 0.01875 0.01027 -0.0872 1.0000 0.3519
-0.750 0.1994 0.01870 0.01050 -0.0878 1.0000 0.4142
-0.500 0.2383 0.01823 0.01063 -0.0904 0.9971 0.5537
-0.250 0.2743 0.01728 0.01043 -0.0918 0.9874 1.0000
0.000 0.3203 0.01759 0.01049 -0.0959 0.9783 1.0000
0.250 0.3689 0.01787 0.01058 -0.1004 0.9708 1.0000
0.500 0.4100 0.01806 0.01065 -0.1035 0.9595 1.0000
0.750 0.4505 0.01823 0.01074 -0.1063 0.9485 1.0000
1.000 0.4923 0.01834 0.01079 -0.1093 0.9382 1.0000
1.250 0.5385 0.01832 0.01076 -0.1129 0.9299 1.0000
1.500 0.5760 0.01835 0.01079 -0.1149 0.9180 1.0000
1.750 0.6145 0.01833 0.01079 -0.1169 0.9067 1.0000
2.000 0.6564 0.01820 0.01072 -0.1194 0.8972 1.0000
2.250 0.6987 0.01794 0.01052 -0.1218 0.8883 1.0000
2.500 0.7330 0.01785 0.01049 -0.1226 0.8758 1.0000
2.750 0.7671 0.01771 0.01046 -0.1232 0.8633 1.0000
3.000 0.8027 0.01723 0.01006 -0.1234 0.8486 1.0000
3.250 0.8386 0.01647 0.00935 -0.1230 0.8312 1.0000
3.500 0.8655 0.01622 0.00916 -0.1216 0.8097 1.0000
3.750 0.8949 0.01602 0.00907 -0.1207 0.7914 1.0000
4.000 0.9227 0.01592 0.00903 -0.1196 0.7717 1.0000
4.250 0.9488 0.01589 0.00907 -0.1183 0.7492 1.0000
4.500 0.9742 0.01589 0.00911 -0.1167 0.7241 1.0000
4.750 0.9988 0.01588 0.00917 -0.1149 0.6943 1.0000
5.000 1.0219 0.01589 0.00916 -0.1128 0.6575 1.0000
5.250 1.0430 0.01601 0.00923 -0.1104 0.6109 1.0000
5.500 1.0626 0.01628 0.00939 -0.1078 0.5531 1.0000
5.750 1.0790 0.01685 0.00970 -0.1048 0.4666 1.0000
6.000 1.0856 0.01852 0.01036 -0.1008 0.2956 1.0000
6.250 1.0886 0.02140 0.01212 -0.0970 0.1674 1.0000
6.500 1.0985 0.02374 0.01399 -0.0939 0.1158 1.0000
6.750 1.1131 0.02560 0.01565 -0.0916 0.0933 1.0000
7.000 1.1314 0.02754 0.01749 -0.0898 0.0809 1.0000
7.250 1.1520 0.02949 0.01933 -0.0886 0.0708 1.0000
7.500 1.1765 0.03139 0.02148 -0.0875 0.0645 1.0000
7.750 1.2021 0.03371 0.02383 -0.0868 0.0603 1.0000
8.000 1.2295 0.03737 0.02760 -0.0865 0.0574 1.0000
8.250 1.2493 0.03946 0.03020 -0.0847 0.0543 1.0000
8.500 1.2683 0.04238 0.03355 -0.0829 0.0523 1.0000
8.750 1.2838 0.04605 0.03772 -0.0808 0.0520 1.0000
9.000 1.2943 0.05029 0.04251 -0.0781 0.0524 1.0000
9.250 1.2994 0.05496 0.04773 -0.0750 0.0536 1.0000
9.500 1.3009 0.05989 0.05314 -0.0720 0.0550 1.0000
9.750 1.2997 0.06487 0.05847 -0.0692 0.0562 1.0000
10.000 1.2959 0.06999 0.06387 -0.0665 0.0569 1.0000
10.250 1.3003 0.07679 0.07080 -0.0655 0.0581 1.0000
10.500 1.2344 0.08106 0.07599 -0.0571 0.0670 1.0000
10.750 1.2292 0.08674 0.08171 -0.0559 0.0691 1.0000
11.000 1.0770 0.08010 0.07546 -0.0396 0.0629 1.0000
11.250 1.0405 0.08618 0.08170 -0.0400 0.0631 1.0000
11.500 1.0018 0.09325 0.08892 -0.0422 0.0634 1.0000
11.750 0.9584 0.10208 0.09786 -0.0467 0.0641 1.0000
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Polar data table (+)
Polar graphs
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