CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 50,000 Max Cl/Cd: 32.86 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkx-il-50000.txt Download as CSV file: xf-clarkx-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK X AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3648 0.10761 0.10039 -0.0260 1.0000 0.2852
-8.500 -0.3449 0.10290 0.09567 -0.0249 1.0000 0.2931
-8.250 -0.3774 0.10353 0.09651 -0.0240 1.0000 0.3021
-8.000 -0.3494 0.09847 0.09141 -0.0226 1.0000 0.3149
-7.750 -0.3461 0.09564 0.08864 -0.0211 1.0000 0.3257
-7.500 -0.3847 0.09643 0.08966 -0.0180 1.0000 0.3344
-7.250 -0.3718 0.09298 0.08623 -0.0160 1.0000 0.3495
-7.000 -0.3593 0.08954 0.08282 -0.0142 1.0000 0.3617
-6.750 -0.3703 0.08775 0.08114 -0.0110 1.0000 0.3721
-6.500 -0.4104 0.08841 0.08202 -0.0052 1.0000 0.3828
-6.250 -0.3964 0.08500 0.07861 -0.0032 1.0000 0.3965
-6.000 -0.3989 0.08271 0.07639 0.0001 1.0000 0.4084
-5.750 -0.4115 0.08108 0.07487 0.0040 1.0000 0.4223
-5.500 -0.4183 0.07925 0.07312 0.0077 1.0000 0.4394
-5.000 -0.4637 0.05622 0.04904 -0.0321 1.0000 0.2059
-4.750 -0.4461 0.05028 0.04254 -0.0355 1.0000 0.1926
-4.500 -0.4269 0.04679 0.03866 -0.0366 1.0000 0.1899
-4.250 -0.4059 0.04360 0.03515 -0.0374 1.0000 0.1878
-4.000 -0.3821 0.04057 0.03166 -0.0385 1.0000 0.1863
-3.750 -0.3571 0.03812 0.02863 -0.0394 1.0000 0.1894
-3.500 -0.3332 0.03620 0.02638 -0.0398 1.0000 0.1937
-3.250 -0.3098 0.03474 0.02473 -0.0399 1.0000 0.1981
-3.000 -0.2847 0.03340 0.02298 -0.0401 1.0000 0.2051
-2.750 -0.2622 0.03244 0.02196 -0.0400 1.0000 0.2144
-2.500 -0.2373 0.03147 0.02068 -0.0401 1.0000 0.2240
-2.250 -0.2140 0.03085 0.01992 -0.0399 1.0000 0.2380
-2.000 -0.1912 0.03030 0.01938 -0.0398 1.0000 0.2548
-1.750 -0.1685 0.02979 0.01893 -0.0395 1.0000 0.2750
-1.500 -0.1449 0.02938 0.01859 -0.0393 1.0000 0.3073
-1.250 -0.1186 0.02879 0.01822 -0.0396 1.0000 0.3625
-1.000 -0.0886 0.02720 0.01792 -0.0398 1.0000 0.5426
-0.750 -0.0818 0.02572 0.01765 -0.0348 1.0000 1.0000
-0.500 -0.0600 0.02636 0.01778 -0.0351 1.0000 1.0000
-0.250 -0.0398 0.02704 0.01813 -0.0353 1.0000 1.0000
0.000 0.0064 0.02827 0.01896 -0.0402 0.9894 1.0000
0.250 0.0526 0.02950 0.01989 -0.0451 0.9768 1.0000
0.500 0.0957 0.03064 0.02078 -0.0493 0.9638 1.0000
0.750 0.1369 0.03173 0.02167 -0.0530 0.9504 1.0000
1.000 0.1773 0.03278 0.02255 -0.0565 0.9369 1.0000
1.250 0.2177 0.03380 0.02343 -0.0599 0.9230 1.0000
1.500 0.2582 0.03477 0.02429 -0.0631 0.9091 1.0000
1.750 0.2967 0.03567 0.02511 -0.0658 0.8949 1.0000
2.000 0.3297 0.03650 0.02587 -0.0675 0.8800 1.0000
2.250 0.3621 0.03731 0.02664 -0.0690 0.8650 1.0000
2.500 0.3942 0.03811 0.02741 -0.0704 0.8499 1.0000
2.750 0.4261 0.03888 0.02816 -0.0716 0.8346 1.0000
3.000 0.4577 0.03963 0.02892 -0.0727 0.8192 1.0000
3.250 0.4894 0.04033 0.02963 -0.0736 0.8037 1.0000
3.500 0.5210 0.04097 0.03030 -0.0744 0.7880 1.0000
3.750 0.5528 0.04156 0.03094 -0.0750 0.7721 1.0000
4.000 0.5853 0.04205 0.03147 -0.0755 0.7562 1.0000
4.250 0.6182 0.04243 0.03191 -0.0759 0.7402 1.0000
4.500 0.6518 0.04266 0.03224 -0.0762 0.7241 1.0000
4.750 0.6868 0.04268 0.03234 -0.0763 0.7081 1.0000
5.000 0.7227 0.04250 0.03227 -0.0762 0.6922 1.0000
5.250 0.7596 0.04211 0.03200 -0.0760 0.6764 1.0000
5.500 0.7957 0.04161 0.03161 -0.0754 0.6607 1.0000
5.750 0.8310 0.04106 0.03120 -0.0747 0.6450 1.0000
6.000 0.8663 0.04047 0.03074 -0.0740 0.6293 1.0000
6.250 0.9031 0.03974 0.03016 -0.0732 0.6134 1.0000
6.500 0.9219 0.04037 0.03089 -0.0714 0.5950 1.0000
6.750 0.9458 0.04064 0.03128 -0.0699 0.5774 1.0000
7.000 0.9746 0.04060 0.03137 -0.0687 0.5604 1.0000
7.250 1.0045 0.04053 0.03145 -0.0676 0.5435 1.0000
7.500 1.0343 0.04054 0.03159 -0.0665 0.5267 1.0000
7.750 1.0622 0.04080 0.03198 -0.0655 0.5103 1.0000
8.000 1.0892 0.04119 0.03252 -0.0644 0.4940 1.0000
8.250 1.1140 0.04179 0.03325 -0.0631 0.4780 1.0000
8.500 1.1375 0.04251 0.03411 -0.0618 0.4622 1.0000
8.750 1.1718 0.04219 0.03391 -0.0610 0.4443 1.0000
9.000 1.1964 0.04191 0.03370 -0.0590 0.4222 1.0000
9.250 1.2278 0.03951 0.03115 -0.0564 0.3882 1.0000
9.500 1.2461 0.03847 0.02999 -0.0533 0.3576 1.0000
9.750 1.2600 0.03835 0.02983 -0.0503 0.3302 1.0000
10.000 1.2648 0.03861 0.03003 -0.0463 0.3003 1.0000
10.250 1.2582 0.03943 0.03079 -0.0412 0.2672 1.0000
10.500 1.2441 0.04075 0.03186 -0.0354 0.2313 1.0000
10.750 1.2302 0.04285 0.03355 -0.0303 0.1967 1.0000
11.000 1.2246 0.04525 0.03559 -0.0267 0.1694 1.0000
11.250 1.2246 0.04793 0.03832 -0.0240 0.1503 1.0000
11.500 1.2321 0.05041 0.04077 -0.0220 0.1361 1.0000
11.750 1.2438 0.05281 0.04314 -0.0204 0.1250 1.0000
12.000 1.2602 0.05533 0.04569 -0.0192 0.1165 1.0000
12.250 1.2683 0.05861 0.04925 -0.0177 0.1113 1.0000
12.500 1.2701 0.06175 0.05265 -0.0160 0.1070 1.0000
12.750 1.2897 0.06472 0.05553 -0.0154 0.1017 1.0000
13.000 1.2759 0.06870 0.05992 -0.0134 0.1007 1.0000
13.250 1.2597 0.07313 0.06470 -0.0120 0.1001 1.0000
13.500 1.2396 0.07806 0.06996 -0.0112 0.1000 1.0000
13.750 1.2154 0.08360 0.07579 -0.0112 0.1001 1.0000
14.000 1.1881 0.08989 0.08232 -0.0122 0.1006 1.0000
14.250 1.1590 0.09698 0.08961 -0.0144 0.1013 1.0000
14.500 1.1300 0.10484 0.09764 -0.0174 0.1020 1.0000
14.750 0.9382 0.15435 0.14711 -0.0515 0.1298 1.0000
15.000 0.9430 0.15912 0.15192 -0.0525 0.1285 1.0000
15.250 0.8865 0.18397 0.17654 -0.0706 0.1873 1.0000
15.500 0.9123 0.18284 0.17549 -0.0663 0.1564 1.0000
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Polar data table (+)
Polar graphs
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