CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 100,000 Max Cl/Cd: 54.69 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkk-il-100000-n5.txt Download as CSV file: xf-clarkk-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4392 0.08905 0.08376 -0.0502 1.0000 0.0716
-9.250 -0.4322 0.08673 0.08147 -0.0483 1.0000 0.0709
-9.000 -0.4332 0.08403 0.07882 -0.0471 1.0000 0.0700
-8.750 -0.4448 0.08095 0.07582 -0.0463 1.0000 0.0691
-8.500 -0.4672 0.07782 0.07280 -0.0452 1.0000 0.0684
-8.250 -0.4897 0.07360 0.06864 -0.0455 1.0000 0.0678
-8.000 -0.5117 0.06892 0.06395 -0.0458 1.0000 0.0674
-7.750 -0.5107 0.06015 0.05489 -0.0537 0.9935 0.0674
-7.500 -0.4994 0.05231 0.04657 -0.0603 0.9853 0.0671
-7.250 -0.4828 0.04690 0.04066 -0.0642 0.9778 0.0677
-7.000 -0.4609 0.04272 0.03591 -0.0672 0.9717 0.0690
-6.750 -0.4370 0.03952 0.03223 -0.0690 0.9653 0.0694
-6.500 -0.4102 0.03687 0.02912 -0.0706 0.9598 0.0697
-6.250 -0.3828 0.03486 0.02664 -0.0719 0.9537 0.0706
-6.000 -0.3507 0.03338 0.02464 -0.0736 0.9493 0.0716
-5.750 -0.3245 0.03163 0.02260 -0.0741 0.9424 0.0720
-5.500 -0.2909 0.02989 0.02060 -0.0759 0.9385 0.0723
-5.250 -0.2624 0.02849 0.01900 -0.0765 0.9322 0.0726
-5.000 -0.2304 0.02719 0.01751 -0.0777 0.9269 0.0730
-4.750 -0.1953 0.02592 0.01614 -0.0794 0.9234 0.0742
-4.500 -0.1691 0.02504 0.01517 -0.0793 0.9154 0.0754
-4.250 -0.1358 0.02413 0.01416 -0.0805 0.9105 0.0764
-4.000 -0.1041 0.02333 0.01325 -0.0812 0.9050 0.0768
-3.750 -0.0756 0.02265 0.01249 -0.0813 0.8975 0.0772
-3.500 -0.0416 0.02192 0.01171 -0.0824 0.8930 0.0776
-3.250 -0.0149 0.02138 0.01114 -0.0822 0.8850 0.0781
-3.000 0.0159 0.02080 0.01053 -0.0826 0.8788 0.0788
-2.750 0.0477 0.02025 0.00996 -0.0833 0.8735 0.0795
-2.500 0.0731 0.01986 0.00957 -0.0827 0.8646 0.0806
-2.250 0.1050 0.01940 0.00908 -0.0833 0.8591 0.0823
-2.000 0.1303 0.01913 0.00878 -0.0828 0.8501 0.0835
-1.750 0.1601 0.01865 0.00830 -0.0830 0.8437 0.0848
-1.500 0.1867 0.01834 0.00798 -0.0826 0.8353 0.0858
-1.250 0.2154 0.01802 0.00764 -0.0826 0.8278 0.0871
-1.000 0.2433 0.01777 0.00737 -0.0824 0.8198 0.0887
-0.750 0.2714 0.01755 0.00712 -0.0822 0.8115 0.0905
-0.500 0.2994 0.01736 0.00691 -0.0820 0.8032 0.0928
-0.250 0.3274 0.01718 0.00671 -0.0818 0.7945 0.0958
0.000 0.3546 0.01699 0.00658 -0.0814 0.7854 0.1030
0.250 0.3825 0.01645 0.00651 -0.0814 0.7769 0.2136
0.500 0.4087 0.01622 0.00650 -0.0810 0.7667 0.2767
0.750 0.4370 0.01568 0.00640 -0.0810 0.7585 0.4072
1.000 0.4584 0.01515 0.00651 -0.0796 0.7470 0.5847
1.250 0.4864 0.01449 0.00663 -0.0783 0.7371 0.8486
1.500 0.5445 0.01430 0.00645 -0.0839 0.7260 1.0000
1.750 0.5683 0.01439 0.00646 -0.0829 0.7123 1.0000
2.000 0.5927 0.01447 0.00644 -0.0820 0.6982 1.0000
2.250 0.6174 0.01454 0.00642 -0.0811 0.6840 1.0000
2.500 0.6423 0.01463 0.00643 -0.0803 0.6698 1.0000
2.750 0.6674 0.01473 0.00645 -0.0795 0.6561 1.0000
3.000 0.6927 0.01485 0.00649 -0.0788 0.6427 1.0000
3.250 0.7168 0.01500 0.00660 -0.0779 0.6280 1.0000
3.500 0.7411 0.01516 0.00671 -0.0771 0.6132 1.0000
3.750 0.7654 0.01533 0.00685 -0.0762 0.5981 1.0000
4.000 0.7897 0.01552 0.00699 -0.0754 0.5827 1.0000
4.250 0.8137 0.01572 0.00715 -0.0745 0.5668 1.0000
4.500 0.8376 0.01595 0.00734 -0.0736 0.5504 1.0000
4.750 0.8612 0.01619 0.00754 -0.0727 0.5335 1.0000
5.000 0.8845 0.01646 0.00777 -0.0717 0.5161 1.0000
5.250 0.9075 0.01676 0.00804 -0.0707 0.4984 1.0000
5.500 0.9300 0.01708 0.00832 -0.0697 0.4801 1.0000
5.750 0.9523 0.01743 0.00864 -0.0686 0.4616 1.0000
6.000 0.9741 0.01781 0.00900 -0.0675 0.4427 1.0000
6.250 0.9955 0.01821 0.00938 -0.0664 0.4236 1.0000
6.500 1.0166 0.01865 0.00981 -0.0652 0.4047 1.0000
6.750 1.0373 0.01911 0.01025 -0.0640 0.3869 1.0000
7.000 1.0579 0.01961 0.01073 -0.0627 0.3702 1.0000
7.250 1.0782 0.02014 0.01125 -0.0615 0.3543 1.0000
7.500 1.0980 0.02070 0.01181 -0.0602 0.3389 1.0000
7.750 1.1168 0.02128 0.01238 -0.0588 0.3229 1.0000
8.000 1.1341 0.02190 0.01297 -0.0573 0.3052 1.0000
8.250 1.1497 0.02256 0.01360 -0.0555 0.2862 1.0000
8.500 1.1644 0.02326 0.01424 -0.0536 0.2678 1.0000
8.750 1.1785 0.02398 0.01494 -0.0517 0.2497 1.0000
9.000 1.1915 0.02472 0.01568 -0.0497 0.2301 1.0000
9.250 1.2028 0.02549 0.01646 -0.0474 0.2118 1.0000
9.500 1.2142 0.02633 0.01733 -0.0453 0.1942 1.0000
9.750 1.2242 0.02728 0.01828 -0.0431 0.1737 1.0000
10.000 1.2327 0.02839 0.01935 -0.0409 0.1464 1.0000
10.250 1.2351 0.02999 0.02074 -0.0383 0.1082 1.0000
10.500 1.2326 0.03214 0.02260 -0.0355 0.0776 1.0000
10.750 1.2323 0.03422 0.02461 -0.0331 0.0624 1.0000
11.000 1.2326 0.03634 0.02671 -0.0309 0.0545 1.0000
11.250 1.2342 0.03840 0.02885 -0.0291 0.0494 1.0000
11.500 1.2327 0.04079 0.03128 -0.0274 0.0461 1.0000
11.750 1.2339 0.04304 0.03368 -0.0261 0.0434 1.0000
12.000 1.2331 0.04555 0.03633 -0.0249 0.0414 1.0000
12.250 1.2307 0.04833 0.03923 -0.0240 0.0399 1.0000
12.500 1.2258 0.05147 0.04247 -0.0232 0.0385 1.0000
12.750 1.2195 0.05486 0.04595 -0.0227 0.0374 1.0000
13.000 1.2178 0.05789 0.04917 -0.0224 0.0363 1.0000
13.250 1.2152 0.06109 0.05252 -0.0222 0.0351 1.0000
13.500 1.2121 0.06443 0.05600 -0.0222 0.0341 1.0000
13.750 1.2093 0.06783 0.05952 -0.0223 0.0332 1.0000
14.000 1.2068 0.07122 0.06302 -0.0224 0.0324 1.0000
14.250 1.2050 0.07458 0.06648 -0.0225 0.0317 1.0000
14.500 1.2036 0.07791 0.06987 -0.0227 0.0309 1.0000
14.750 1.2036 0.08096 0.07297 -0.0226 0.0302 1.0000
15.000 1.2058 0.08372 0.07577 -0.0222 0.0293 1.0000
15.250 1.2057 0.08715 0.07940 -0.0227 0.0287 1.0000
15.500 1.2050 0.09074 0.08317 -0.0234 0.0280 1.0000
15.750 1.2036 0.09448 0.08709 -0.0241 0.0274 1.0000
16.000 1.2020 0.09832 0.09108 -0.0250 0.0269 1.0000
16.250 1.1995 0.10237 0.09530 -0.0260 0.0265 1.0000
16.500 1.1959 0.10669 0.09979 -0.0274 0.0261 1.0000
16.750 1.1907 0.11143 0.10470 -0.0292 0.0258 1.0000
17.000 1.1842 0.11654 0.10998 -0.0314 0.0255 1.0000
17.250 1.1763 0.12204 0.11565 -0.0341 0.0252 1.0000
17.500 1.1671 0.12799 0.12178 -0.0372 0.0250 1.0000
17.750 1.1561 0.13457 0.12854 -0.0409 0.0248 1.0000
18.000 1.1427 0.14199 0.13615 -0.0455 0.0247 1.0000
18.250 1.1241 0.15123 0.14560 -0.0514 0.0247 1.0000
18.500 1.0886 0.16613 0.16080 -0.0614 0.0252 1.0000
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Polar data table (+)
Polar graphs
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