CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 200,000 Max Cl/Cd: 74.82 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkz-il-200000.txt Download as CSV file: xf-clarkz-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3510 0.09263 0.08919 -0.0331 1.0000 0.0642
-8.000 -0.3674 0.09154 0.08819 -0.0298 1.0000 0.0648
-7.750 -0.3853 0.09042 0.08714 -0.0268 0.9997 0.0654
-7.500 -0.3707 0.08549 0.08221 -0.0357 0.9933 0.0684
-7.250 -0.3504 0.07467 0.07126 -0.0578 0.9827 0.0717
-7.000 -0.3296 0.07254 0.06915 -0.0569 0.9778 0.0728
-6.750 -0.3039 0.06929 0.06588 -0.0604 0.9732 0.0747
-6.500 -0.2773 0.06458 0.06107 -0.0679 0.9672 0.0784
-6.250 -0.2536 0.05636 0.05250 -0.0799 0.9582 0.0835
-6.000 -0.2216 0.05372 0.04988 -0.0825 0.9561 0.0852
-5.750 -0.2002 0.05125 0.04735 -0.0839 0.9474 0.0879
-5.500 -0.1666 0.04561 0.04121 -0.0914 0.9426 0.0965
-5.250 -0.1312 0.04328 0.03895 -0.0941 0.9407 0.0993
-5.000 -0.1100 0.04090 0.03601 -0.0956 0.9296 0.1099
-4.750 -0.0777 0.03768 0.03289 -0.0978 0.9267 0.1120
-4.500 -0.0578 0.02804 0.02190 -0.0972 0.9169 0.0726
-4.250 -0.0238 0.02879 0.02299 -0.0991 0.9122 0.0865
-4.000 0.0081 0.02296 0.01611 -0.0990 0.9079 0.0663
-3.750 0.0326 0.02149 0.01437 -0.0981 0.8985 0.0661
-3.500 0.0659 0.01988 0.01247 -0.0986 0.8938 0.0656
-3.250 0.0916 0.01887 0.01128 -0.0978 0.8846 0.0659
-3.000 0.1226 0.01786 0.01012 -0.0978 0.8785 0.0669
-2.750 0.1494 0.01712 0.00929 -0.0972 0.8698 0.0681
-2.500 0.1788 0.01651 0.00856 -0.0969 0.8624 0.0703
-2.250 0.2047 0.01569 0.00778 -0.0963 0.8535 0.0732
-2.000 0.2328 0.01511 0.00721 -0.0959 0.8456 0.0765
-1.750 0.2587 0.01468 0.00676 -0.0951 0.8359 0.0803
-1.500 0.2864 0.01407 0.00616 -0.0946 0.8280 0.0863
-1.250 0.3115 0.01370 0.00584 -0.0938 0.8175 0.0975
-1.000 0.3389 0.01312 0.00539 -0.0933 0.8095 0.1320
-0.750 0.3620 0.01237 0.00514 -0.0925 0.7987 0.2489
-0.500 0.3764 0.01087 0.00514 -0.0899 0.7895 0.6668
-0.250 0.4531 0.01026 0.00505 -0.0980 0.7811 0.9951
0.000 0.4847 0.01027 0.00491 -0.0986 0.7703 1.0000
0.250 0.5106 0.01029 0.00475 -0.0979 0.7606 1.0000
0.500 0.5343 0.01035 0.00471 -0.0969 0.7484 1.0000
0.750 0.5587 0.01042 0.00466 -0.0961 0.7369 1.0000
1.000 0.5842 0.01048 0.00458 -0.0953 0.7262 1.0000
1.250 0.6085 0.01055 0.00456 -0.0944 0.7139 1.0000
1.500 0.6327 0.01065 0.00457 -0.0935 0.7014 1.0000
1.750 0.6575 0.01075 0.00457 -0.0926 0.6893 1.0000
2.000 0.6828 0.01086 0.00456 -0.0919 0.6773 1.0000
2.250 0.7071 0.01097 0.00459 -0.0910 0.6639 1.0000
2.500 0.7313 0.01110 0.00466 -0.0901 0.6501 1.0000
2.750 0.7558 0.01124 0.00473 -0.0893 0.6363 1.0000
3.000 0.7804 0.01139 0.00479 -0.0884 0.6224 1.0000
3.250 0.8051 0.01156 0.00487 -0.0876 0.6085 1.0000
3.500 0.8297 0.01174 0.00497 -0.0868 0.5944 1.0000
3.750 0.8542 0.01194 0.00507 -0.0860 0.5800 1.0000
4.000 0.8782 0.01214 0.00522 -0.0852 0.5650 1.0000
4.250 0.9021 0.01236 0.00538 -0.0843 0.5497 1.0000
4.500 0.9258 0.01258 0.00554 -0.0834 0.5339 1.0000
4.750 0.9491 0.01282 0.00570 -0.0825 0.5176 1.0000
5.000 0.9722 0.01307 0.00588 -0.0815 0.5011 1.0000
5.250 0.9952 0.01334 0.00608 -0.0805 0.4849 1.0000
5.500 1.0179 0.01362 0.00630 -0.0796 0.4689 1.0000
5.750 1.0407 0.01391 0.00655 -0.0786 0.4536 1.0000
6.000 1.0637 0.01422 0.00682 -0.0777 0.4398 1.0000
6.250 1.0866 0.01454 0.00712 -0.0769 0.4270 1.0000
6.500 1.1094 0.01490 0.00743 -0.0760 0.4148 1.0000
6.750 1.1317 0.01525 0.00774 -0.0750 0.4020 1.0000
7.000 1.1537 0.01557 0.00808 -0.0740 0.3887 1.0000
7.250 1.1754 0.01592 0.00844 -0.0730 0.3756 1.0000
7.500 1.1967 0.01629 0.00881 -0.0719 0.3629 1.0000
7.750 1.2173 0.01668 0.00919 -0.0708 0.3499 1.0000
8.000 1.2369 0.01710 0.00958 -0.0694 0.3360 1.0000
8.250 1.2557 0.01752 0.01001 -0.0680 0.3210 1.0000
8.500 1.2735 0.01796 0.01046 -0.0664 0.3045 1.0000
8.750 1.2903 0.01843 0.01095 -0.0647 0.2861 1.0000
9.000 1.3050 0.01899 0.01149 -0.0627 0.2648 1.0000
9.250 1.3151 0.01971 0.01213 -0.0600 0.2410 1.0000
9.500 1.3218 0.02064 0.01293 -0.0570 0.2143 1.0000
9.750 1.3280 0.02175 0.01390 -0.0540 0.1901 1.0000
10.000 1.3337 0.02297 0.01501 -0.0512 0.1730 1.0000
10.250 1.3412 0.02417 0.01615 -0.0488 0.1609 1.0000
10.500 1.3485 0.02544 0.01738 -0.0464 0.1525 1.0000
10.750 1.3581 0.02660 0.01855 -0.0445 0.1453 1.0000
11.000 1.3663 0.02793 0.01984 -0.0425 0.1397 1.0000
11.250 1.3778 0.02902 0.02101 -0.0409 0.1343 1.0000
11.500 1.3861 0.03037 0.02232 -0.0392 0.1295 1.0000
11.750 1.3965 0.03164 0.02365 -0.0377 0.1252 1.0000
12.000 1.4070 0.03285 0.02495 -0.0363 0.1210 1.0000
12.250 1.4158 0.03423 0.02634 -0.0349 0.1172 1.0000
12.500 1.4258 0.03567 0.02776 -0.0335 0.1138 1.0000
12.750 1.4356 0.03700 0.02924 -0.0323 0.1108 1.0000
13.000 1.4447 0.03841 0.03076 -0.0312 0.1077 1.0000
13.250 1.4524 0.03995 0.03233 -0.0301 0.1046 1.0000
13.500 1.4615 0.04153 0.03388 -0.0289 0.1013 1.0000
13.750 1.4670 0.04326 0.03581 -0.0279 0.0986 1.0000
14.000 1.4726 0.04504 0.03771 -0.0271 0.0956 1.0000
14.250 1.4776 0.04690 0.03964 -0.0263 0.0929 1.0000
14.500 1.4858 0.04861 0.04129 -0.0252 0.0897 1.0000
14.750 1.4868 0.05091 0.04383 -0.0247 0.0875 1.0000
15.000 1.4883 0.05326 0.04634 -0.0243 0.0847 1.0000
15.250 1.4892 0.05571 0.04888 -0.0240 0.0818 1.0000
15.500 1.4920 0.05797 0.05110 -0.0234 0.0785 1.0000
15.750 1.4875 0.06133 0.05474 -0.0238 0.0757 1.0000
16.000 1.4841 0.06468 0.05824 -0.0244 0.0723 1.0000
16.250 1.4802 0.06805 0.06160 -0.0248 0.0689 1.0000
16.500 1.4728 0.07230 0.06610 -0.0259 0.0650 1.0000
16.750 1.4655 0.07666 0.07058 -0.0273 0.0611 1.0000
17.000 1.4561 0.08135 0.07537 -0.0286 0.0571 1.0000
17.250 1.4470 0.08623 0.08037 -0.0303 0.0532 1.0000
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