CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 50,000 Max Cl/Cd: 36.2 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkz-il-50000-n5.txt Download as CSV file: xf-clarkz-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Z 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3233 0.11293 0.10557 -0.0366 1.0000 0.1390
-9.000 -0.3430 0.11204 0.10483 -0.0378 1.0000 0.1403
-8.750 -0.3610 0.11075 0.10371 -0.0378 1.0000 0.1407
-8.500 -0.3629 0.10762 0.10069 -0.0366 1.0000 0.1413
-8.250 -0.3452 0.10326 0.09633 -0.0347 1.0000 0.1427
-8.000 -0.3386 0.10046 0.09357 -0.0326 1.0000 0.1450
-7.750 -0.3432 0.09850 0.09170 -0.0306 1.0000 0.1472
-7.500 -0.3552 0.09693 0.09024 -0.0282 1.0000 0.1491
-7.000 -0.4197 0.08725 0.08067 -0.0344 1.0000 0.0951
-6.750 -0.4121 0.08619 0.07970 -0.0297 1.0000 0.0983
-6.250 -0.4091 0.07329 0.06640 -0.0422 0.9923 0.0809
-6.000 -0.3859 0.06940 0.06243 -0.0454 0.9856 0.0797
-5.750 -0.3626 0.06502 0.05789 -0.0496 0.9781 0.0783
-5.500 -0.3357 0.06028 0.05289 -0.0546 0.9713 0.0770
-5.250 -0.3119 0.05602 0.04832 -0.0583 0.9629 0.0763
-5.000 -0.2832 0.05207 0.04399 -0.0621 0.9560 0.0771
-4.750 -0.2558 0.04858 0.04009 -0.0649 0.9481 0.0779
-4.500 -0.2240 0.04527 0.03632 -0.0679 0.9418 0.0782
-4.250 -0.1960 0.04251 0.03313 -0.0695 0.9337 0.0782
-4.000 -0.1594 0.03986 0.02999 -0.0723 0.9284 0.0786
-3.750 -0.1325 0.03789 0.02760 -0.0729 0.9196 0.0792
-3.500 -0.0953 0.03595 0.02509 -0.0750 0.9137 0.0813
-3.250 -0.0668 0.03475 0.02382 -0.0757 0.9054 0.0838
-3.000 -0.0317 0.03357 0.02247 -0.0773 0.8986 0.0867
-2.750 0.0014 0.03241 0.02106 -0.0783 0.8912 0.0891
-2.250 0.0735 0.03035 0.01861 -0.0810 0.8776 0.0966
-2.000 0.1023 0.02977 0.01799 -0.0811 0.8679 0.1030
-1.750 0.1433 0.02889 0.01698 -0.0830 0.8628 0.1113
-1.500 0.1684 0.02844 0.01650 -0.0824 0.8517 0.1208
-1.250 0.2051 0.02772 0.01574 -0.0836 0.8451 0.1400
-1.000 0.2318 0.02714 0.01533 -0.0834 0.8346 0.1683
-0.750 0.2635 0.02620 0.01479 -0.0842 0.8265 0.2391
-0.500 0.2909 0.02368 0.01477 -0.0826 0.8189 0.8504
-0.250 0.3396 0.02352 0.01421 -0.0860 0.8107 1.0000
0.000 0.3678 0.02359 0.01399 -0.0857 0.8001 1.0000
0.250 0.3934 0.02373 0.01390 -0.0851 0.7887 1.0000
0.500 0.4286 0.02360 0.01354 -0.0858 0.7809 1.0000
0.750 0.4512 0.02381 0.01359 -0.0847 0.7681 1.0000
1.000 0.4777 0.02393 0.01355 -0.0841 0.7570 1.0000
1.250 0.5105 0.02383 0.01329 -0.0844 0.7482 1.0000
1.500 0.5334 0.02406 0.01340 -0.0833 0.7353 1.0000
1.750 0.5596 0.02418 0.01342 -0.0827 0.7239 1.0000
2.000 0.5917 0.02409 0.01321 -0.0828 0.7147 1.0000
2.250 0.6144 0.02435 0.01340 -0.0817 0.7015 1.0000
2.500 0.6395 0.02454 0.01352 -0.0809 0.6894 1.0000
2.750 0.6696 0.02452 0.01341 -0.0807 0.6793 1.0000
3.000 0.6946 0.02472 0.01356 -0.0799 0.6668 1.0000
3.250 0.7180 0.02500 0.01381 -0.0790 0.6538 1.0000
3.500 0.7439 0.02519 0.01395 -0.0783 0.6418 1.0000
3.750 0.7742 0.02518 0.01389 -0.0781 0.6315 1.0000
4.000 0.7961 0.02556 0.01426 -0.0770 0.6178 1.0000
4.250 0.8194 0.02590 0.01459 -0.0760 0.6048 1.0000
4.500 0.8447 0.02616 0.01485 -0.0753 0.5929 1.0000
4.750 0.8737 0.02624 0.01489 -0.0750 0.5820 1.0000
5.000 0.8949 0.02672 0.01539 -0.0739 0.5685 1.0000
5.250 0.9173 0.02715 0.01586 -0.0729 0.5558 1.0000
5.500 0.9419 0.02749 0.01621 -0.0721 0.5438 1.0000
5.750 0.9696 0.02768 0.01637 -0.0716 0.5328 1.0000
6.000 0.9896 0.02824 0.01701 -0.0704 0.5195 1.0000
6.250 1.0109 0.02876 0.01757 -0.0693 0.5068 1.0000
6.500 1.0339 0.02918 0.01802 -0.0683 0.4945 1.0000
6.750 1.0591 0.02948 0.01832 -0.0676 0.4825 1.0000
7.000 1.0796 0.02997 0.01887 -0.0663 0.4689 1.0000
7.250 1.0982 0.03046 0.01939 -0.0647 0.4539 1.0000
7.500 1.1163 0.03087 0.01980 -0.0630 0.4376 1.0000
7.750 1.1332 0.03130 0.02025 -0.0611 0.4207 1.0000
8.000 1.1488 0.03181 0.02076 -0.0592 0.4041 1.0000
8.250 1.1632 0.03243 0.02141 -0.0572 0.3881 1.0000
8.500 1.1766 0.03316 0.02219 -0.0552 0.3729 1.0000
8.750 1.1891 0.03394 0.02306 -0.0531 0.3581 1.0000
9.000 1.2003 0.03478 0.02397 -0.0509 0.3433 1.0000
9.250 1.2092 0.03567 0.02491 -0.0485 0.3287 1.0000
9.500 1.2172 0.03667 0.02595 -0.0460 0.3138 1.0000
9.750 1.2244 0.03777 0.02710 -0.0437 0.2989 1.0000
10.000 1.2304 0.03901 0.02839 -0.0414 0.2839 1.0000
10.250 1.2353 0.04038 0.02980 -0.0392 0.2689 1.0000
10.500 1.2396 0.04189 0.03132 -0.0372 0.2544 1.0000
10.750 1.2438 0.04349 0.03292 -0.0353 0.2409 1.0000
11.000 1.2478 0.04524 0.03469 -0.0335 0.2283 1.0000
11.500 1.2556 0.04917 0.03874 -0.0306 0.2063 1.0000
11.750 1.2621 0.05090 0.04041 -0.0293 0.1976 1.0000
12.000 1.2647 0.05328 0.04294 -0.0282 0.1889 1.0000
12.250 1.2732 0.05499 0.04458 -0.0270 0.1822 1.0000
12.500 1.2763 0.05753 0.04733 -0.0262 0.1758 1.0000
12.750 1.2854 0.05934 0.04919 -0.0252 0.1704 1.0000
13.000 1.2910 0.06167 0.05165 -0.0244 0.1655 1.0000
13.250 1.2915 0.06459 0.05477 -0.0238 0.1608 1.0000
13.500 1.2999 0.06656 0.05680 -0.0230 0.1564 1.0000
13.750 1.3069 0.06884 0.05917 -0.0224 0.1526 1.0000
14.000 1.2981 0.07307 0.06370 -0.0224 0.1497 1.0000
14.250 1.2904 0.07725 0.06812 -0.0226 0.1468 1.0000
14.500 1.2875 0.08084 0.07189 -0.0226 0.1439 1.0000
14.750 1.3133 0.08080 0.07176 -0.0212 0.1400 1.0000
15.000 1.2808 0.08839 0.07971 -0.0232 0.1385 1.0000
15.250 1.2340 0.09902 0.09066 -0.0274 0.1374 1.0000
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Polar data table (+)
Polar graphs
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