CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Y AIRFOIL (clarky-il) Reynolds number: 100,000 Max Cl/Cd: 53.01 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarky-il-100000.txt Download as CSV file: xf-clarky-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Y 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 -0.3474 0.10140 0.09638 -0.0367 1.0000 0.1273
-8.750 -0.3809 0.10037 0.09553 -0.0393 1.0000 0.1308
-8.500 -0.4214 0.09979 0.09515 -0.0389 1.0000 0.1313
-8.250 -0.3699 0.09349 0.08874 -0.0357 1.0000 0.1351
-8.000 -0.3685 0.09146 0.08675 -0.0335 1.0000 0.1389
-7.750 -0.3862 0.09004 0.08545 -0.0311 1.0000 0.1423
-7.500 -0.4177 0.08922 0.08477 -0.0278 1.0000 0.1440
-7.250 -0.4616 0.08774 0.08342 -0.0294 1.0000 0.1460
-7.000 -0.4818 0.08423 0.07996 -0.0300 1.0000 0.1476
-6.750 -0.4620 0.08250 0.07829 -0.0229 1.0000 0.1509
-6.500 -0.4660 0.08065 0.07647 -0.0207 1.0000 0.1552
-6.250 -0.4964 0.07643 0.07214 -0.0280 1.0000 0.1629
-6.000 -0.4869 0.07438 0.07022 -0.0227 1.0000 0.1653
-5.750 -0.4833 0.07245 0.06830 -0.0203 1.0000 0.1693
-5.500 -0.4804 0.06812 0.06384 -0.0253 0.9986 0.1800
-5.250 -0.4492 0.06395 0.05946 -0.0321 0.9922 0.1948
-5.000 -0.4217 0.06129 0.05687 -0.0322 0.9869 0.2008
-4.750 -0.3727 0.04267 0.03658 -0.0508 0.9819 0.1207
-4.500 -0.3344 0.03587 0.02837 -0.0541 0.9768 0.1009
-4.250 -0.2952 0.03304 0.02513 -0.0572 0.9721 0.0999
-4.000 -0.2584 0.03133 0.02290 -0.0593 0.9662 0.1012
-3.750 -0.2209 0.02948 0.02067 -0.0615 0.9603 0.1027
-3.500 -0.1775 0.02785 0.01885 -0.0648 0.9562 0.1046
-3.250 -0.1467 0.02687 0.01776 -0.0656 0.9484 0.1073
-3.000 -0.1049 0.02601 0.01674 -0.0683 0.9429 0.1129
-2.750 -0.0711 0.02520 0.01588 -0.0696 0.9359 0.1198
-2.500 -0.0332 0.02449 0.01516 -0.0716 0.9294 0.1296
-2.250 0.0075 0.02360 0.01442 -0.0740 0.9242 0.1486
-2.000 0.0372 0.02287 0.01400 -0.0746 0.9157 0.1943
-1.750 0.0798 0.02169 0.01361 -0.0777 0.9111 0.3339
-1.500 0.1048 0.02083 0.01363 -0.0774 0.9016 0.5186
-1.250 0.1696 0.01958 0.01355 -0.0816 0.8979 1.0000
-1.000 0.2100 0.01947 0.01315 -0.0838 0.8869 1.0000
-0.750 0.2685 0.01902 0.01241 -0.0888 0.8803 1.0000
-0.500 0.2971 0.01899 0.01222 -0.0887 0.8684 1.0000
-0.250 0.3365 0.01882 0.01188 -0.0905 0.8612 1.0000
0.000 0.3674 0.01875 0.01169 -0.0908 0.8514 1.0000
0.250 0.3960 0.01875 0.01157 -0.0906 0.8414 1.0000
0.500 0.4341 0.01846 0.01117 -0.0918 0.8343 1.0000
0.750 0.4587 0.01851 0.01114 -0.0909 0.8228 1.0000
1.000 0.4950 0.01820 0.01074 -0.0917 0.8154 1.0000
1.250 0.5218 0.01814 0.01061 -0.0910 0.8041 1.0000
1.500 0.5474 0.01813 0.01054 -0.0901 0.7925 1.0000
1.750 0.5797 0.01788 0.01022 -0.0901 0.7833 1.0000
2.000 0.6085 0.01772 0.01001 -0.0896 0.7720 1.0000
2.250 0.6339 0.01769 0.00993 -0.0886 0.7589 1.0000
2.500 0.6607 0.01761 0.00981 -0.0877 0.7459 1.0000
2.750 0.6885 0.01750 0.00966 -0.0870 0.7330 1.0000
3.000 0.7166 0.01739 0.00949 -0.0864 0.7195 1.0000
3.250 0.7438 0.01730 0.00936 -0.0855 0.7046 1.0000
3.500 0.7699 0.01727 0.00928 -0.0846 0.6881 1.0000
3.750 0.7954 0.01729 0.00925 -0.0836 0.6706 1.0000
4.000 0.8211 0.01732 0.00924 -0.0826 0.6524 1.0000
4.250 0.8471 0.01737 0.00921 -0.0817 0.6336 1.0000
4.500 0.8738 0.01746 0.00919 -0.0809 0.6150 1.0000
4.750 0.8972 0.01771 0.00940 -0.0798 0.5947 1.0000
5.000 0.9213 0.01798 0.00962 -0.0788 0.5753 1.0000
5.250 0.9460 0.01829 0.00985 -0.0780 0.5574 1.0000
5.500 0.9706 0.01863 0.01012 -0.0772 0.5405 1.0000
5.750 0.9949 0.01901 0.01045 -0.0763 0.5244 1.0000
6.000 1.0188 0.01941 0.01081 -0.0755 0.5089 1.0000
6.250 1.0422 0.01978 0.01114 -0.0745 0.4930 1.0000
6.500 1.0650 0.02014 0.01146 -0.0735 0.4768 1.0000
6.750 1.0873 0.02051 0.01180 -0.0724 0.4611 1.0000
7.000 1.1094 0.02094 0.01224 -0.0713 0.4465 1.0000
7.250 1.1315 0.02142 0.01276 -0.0703 0.4331 1.0000
7.500 1.1536 0.02191 0.01329 -0.0693 0.4197 1.0000
7.750 1.1755 0.02241 0.01382 -0.0683 0.4065 1.0000
8.000 1.1971 0.02293 0.01435 -0.0672 0.3929 1.0000
8.250 1.2182 0.02347 0.01492 -0.0661 0.3789 1.0000
8.500 1.2388 0.02405 0.01551 -0.0649 0.3645 1.0000
8.750 1.2581 0.02466 0.01615 -0.0635 0.3492 1.0000
9.000 1.2755 0.02531 0.01685 -0.0619 0.3326 1.0000
9.250 1.2908 0.02599 0.01760 -0.0599 0.3146 1.0000
9.500 1.3041 0.02665 0.01830 -0.0576 0.2954 1.0000
9.750 1.3159 0.02731 0.01893 -0.0552 0.2763 1.0000
10.000 1.3249 0.02802 0.01965 -0.0524 0.2575 1.0000
10.250 1.3309 0.02876 0.02046 -0.0492 0.2393 1.0000
10.500 1.3363 0.02954 0.02127 -0.0461 0.2233 1.0000
10.750 1.3413 0.03044 0.02219 -0.0430 0.2094 1.0000
11.000 1.3473 0.03148 0.02322 -0.0403 0.1972 1.0000
11.250 1.3539 0.03261 0.02428 -0.0378 0.1865 1.0000
11.500 1.3594 0.03385 0.02564 -0.0355 0.1760 1.0000
11.750 1.3649 0.03520 0.02707 -0.0333 0.1663 1.0000
12.000 1.3683 0.03666 0.02850 -0.0311 0.1570 1.0000
12.250 1.3687 0.03826 0.03022 -0.0290 0.1473 1.0000
12.500 1.3694 0.04007 0.03217 -0.0271 0.1381 1.0000
12.750 1.3687 0.04207 0.03420 -0.0254 0.1294 1.0000
13.000 1.3644 0.04442 0.03666 -0.0238 0.1196 1.0000
13.250 1.3568 0.04727 0.03965 -0.0225 0.1086 1.0000
13.500 1.3456 0.05070 0.04316 -0.0215 0.0969 1.0000
13.750 1.3323 0.05464 0.04712 -0.0208 0.0856 1.0000
14.000 1.3196 0.05873 0.05120 -0.0202 0.0761 1.0000
14.250 1.3103 0.06255 0.05499 -0.0199 0.0694 1.0000
14.500 1.3050 0.06622 0.05879 -0.0194 0.0635 1.0000
14.750 1.3011 0.06963 0.06219 -0.0193 0.0596 1.0000
15.000 1.2996 0.07289 0.06556 -0.0188 0.0562 1.0000
15.250 1.2970 0.07647 0.06929 -0.0189 0.0533 1.0000
15.500 1.2952 0.07985 0.07272 -0.0191 0.0508 1.0000
15.750 1.2975 0.08261 0.07541 -0.0187 0.0485 1.0000
16.000 1.2921 0.08687 0.07995 -0.0194 0.0471 1.0000
16.250 1.2873 0.09111 0.08441 -0.0200 0.0458 1.0000
16.500 1.2822 0.09546 0.08896 -0.0209 0.0448 1.0000
16.750 1.2755 0.10014 0.09382 -0.0221 0.0440 1.0000
17.000 1.2673 0.10518 0.09905 -0.0238 0.0434 1.0000
17.250 1.2568 0.11077 0.10483 -0.0260 0.0430 1.0000
17.500 1.2419 0.11739 0.11167 -0.0291 0.0428 1.0000
17.750 1.2181 0.12614 0.12069 -0.0340 0.0430 1.0000
18.000 1.1716 0.14084 0.13576 -0.0436 0.0444 1.0000
18.250 1.0657 0.17534 0.17052 -0.0663 0.0498 1.0000
18.500 1.0634 0.18080 0.17597 -0.0691 0.0489 1.0000
18.750 0.9950 0.21955 0.21443 -0.0905 0.0654 1.0000
19.000 1.0031 0.22395 0.21884 -0.0919 0.0673 1.0000
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