CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 500,000 Max Cl/Cd: 91.27 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkk-il-500000-n5.txt Download as CSV file: xf-clarkk-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7985 0.03391 0.03025 -0.0813 0.9907 0.0326
-11.000 -0.7684 0.03392 0.03024 -0.0824 0.9881 0.0329
-10.750 -0.7373 0.03394 0.03025 -0.0837 0.9860 0.0331
-10.500 -0.7063 0.03377 0.03005 -0.0851 0.9842 0.0334
-10.250 -0.6800 0.03340 0.02964 -0.0857 0.9798 0.0339
-10.000 -0.6530 0.03268 0.02884 -0.0868 0.9762 0.0344
-9.750 -0.6272 0.03152 0.02754 -0.0879 0.9726 0.0352
-9.500 -0.6068 0.02972 0.02549 -0.0883 0.9663 0.0364
-9.250 -0.5904 0.02635 0.02151 -0.0886 0.9602 0.0384
-9.000 -0.5660 0.02549 0.02058 -0.0887 0.9542 0.0388
-8.750 -0.5389 0.02483 0.01986 -0.0892 0.9498 0.0391
-8.500 -0.5146 0.02428 0.01924 -0.0890 0.9429 0.0395
-8.250 -0.4885 0.02368 0.01855 -0.0892 0.9374 0.0399
-8.000 -0.4645 0.02300 0.01779 -0.0889 0.9300 0.0403
-7.750 -0.4396 0.02217 0.01682 -0.0888 0.9236 0.0408
-7.500 -0.4155 0.02139 0.01591 -0.0884 0.9158 0.0414
-7.250 -0.3905 0.02063 0.01500 -0.0881 0.9086 0.0421
-7.000 -0.3661 0.01979 0.01400 -0.0877 0.9004 0.0427
-6.750 -0.3410 0.01897 0.01300 -0.0874 0.8925 0.0432
-6.500 -0.3158 0.01824 0.01211 -0.0870 0.8839 0.0437
-6.250 -0.2900 0.01764 0.01135 -0.0867 0.8757 0.0442
-6.000 -0.2638 0.01724 0.01081 -0.0863 0.8671 0.0447
-5.750 -0.2375 0.01682 0.01025 -0.0861 0.8589 0.0449
-5.500 -0.2117 0.01597 0.00931 -0.0858 0.8504 0.0452
-5.250 -0.1856 0.01521 0.00848 -0.0856 0.8423 0.0455
-5.000 -0.1592 0.01465 0.00787 -0.0854 0.8340 0.0458
-4.750 -0.1326 0.01418 0.00735 -0.0852 0.8257 0.0461
-4.500 -0.1058 0.01376 0.00689 -0.0850 0.8173 0.0464
-4.250 -0.0791 0.01338 0.00645 -0.0848 0.8090 0.0467
-4.000 -0.0522 0.01302 0.00606 -0.0846 0.8006 0.0471
-3.750 -0.0253 0.01270 0.00569 -0.0844 0.7923 0.0475
-3.500 0.0018 0.01242 0.00538 -0.0842 0.7839 0.0480
-3.250 0.0287 0.01216 0.00507 -0.0840 0.7755 0.0486
-3.000 0.0557 0.01187 0.00475 -0.0838 0.7671 0.0490
-2.500 0.1097 0.01136 0.00418 -0.0834 0.7501 0.0498
-2.250 0.1366 0.01116 0.00392 -0.0831 0.7415 0.0503
-2.000 0.1637 0.01095 0.00369 -0.0830 0.7325 0.0507
-1.750 0.1906 0.01077 0.00348 -0.0827 0.7238 0.0511
-1.500 0.2178 0.01061 0.00330 -0.0825 0.7143 0.0514
-1.250 0.2448 0.01047 0.00313 -0.0823 0.7050 0.0518
-1.000 0.2718 0.01035 0.00298 -0.0821 0.6948 0.0521
-0.750 0.2989 0.01024 0.00285 -0.0819 0.6845 0.0524
-0.500 0.3259 0.01017 0.00274 -0.0816 0.6738 0.0526
-0.250 0.3521 0.00996 0.00250 -0.0813 0.6604 0.0535
0.000 0.3783 0.00987 0.00236 -0.0809 0.6434 0.0545
0.250 0.4046 0.00983 0.00227 -0.0806 0.6257 0.0555
0.500 0.4313 0.00979 0.00220 -0.0803 0.6111 0.0562
0.750 0.4583 0.00977 0.00214 -0.0801 0.5980 0.0570
1.000 0.4850 0.00977 0.00211 -0.0798 0.5843 0.0579
1.250 0.5117 0.00980 0.00209 -0.0795 0.5702 0.0587
1.500 0.5383 0.00984 0.00209 -0.0792 0.5571 0.0596
1.750 0.5649 0.00989 0.00210 -0.0789 0.5434 0.0604
2.000 0.5913 0.00997 0.00212 -0.0786 0.5287 0.0612
2.250 0.6178 0.01003 0.00215 -0.0783 0.5142 0.0626
2.500 0.6444 0.01010 0.00219 -0.0781 0.5011 0.0648
2.750 0.6707 0.01018 0.00225 -0.0778 0.4872 0.0683
3.250 0.7220 0.01014 0.00246 -0.0771 0.4560 0.2112
3.500 0.7373 0.00874 0.00272 -0.0751 0.4427 0.8017
3.750 0.7808 0.00867 0.00294 -0.0782 0.4240 0.9948
4.000 0.8083 0.00889 0.00308 -0.0782 0.4056 1.0000
4.250 0.8321 0.00913 0.00323 -0.0774 0.3865 1.0000
4.500 0.8559 0.00938 0.00340 -0.0767 0.3683 1.0000
4.750 0.8798 0.00964 0.00358 -0.0760 0.3515 1.0000
5.000 0.9037 0.00991 0.00378 -0.0753 0.3348 1.0000
5.250 0.9270 0.01022 0.00400 -0.0745 0.3160 1.0000
5.500 0.9498 0.01058 0.00425 -0.0736 0.2928 1.0000
5.750 0.9727 0.01094 0.00452 -0.0728 0.2725 1.0000
6.000 0.9960 0.01126 0.00477 -0.0721 0.2571 1.0000
6.250 1.0192 0.01159 0.00505 -0.0713 0.2423 1.0000
6.500 1.0417 0.01198 0.00535 -0.0705 0.2245 1.0000
6.750 1.0638 0.01239 0.00567 -0.0696 0.2068 1.0000
7.000 1.0866 0.01274 0.00597 -0.0688 0.1936 1.0000
7.250 1.1091 0.01311 0.00630 -0.0680 0.1806 1.0000
7.500 1.1308 0.01353 0.00665 -0.0671 0.1643 1.0000
7.750 1.1508 0.01407 0.00706 -0.0659 0.1425 1.0000
8.000 1.1679 0.01480 0.00760 -0.0644 0.1094 1.0000
8.250 1.1806 0.01584 0.00838 -0.0622 0.0698 1.0000
8.500 1.1924 0.01690 0.00923 -0.0599 0.0388 1.0000
8.750 1.2079 0.01757 0.00986 -0.0580 0.0306 1.0000
9.000 1.2251 0.01811 0.01043 -0.0564 0.0272 1.0000
9.250 1.2413 0.01871 0.01105 -0.0547 0.0248 1.0000
9.500 1.2573 0.01934 0.01172 -0.0530 0.0229 1.0000
9.750 1.2740 0.01992 0.01234 -0.0515 0.0215 1.0000
10.000 1.2894 0.02059 0.01305 -0.0499 0.0202 1.0000
10.250 1.3033 0.02136 0.01386 -0.0481 0.0190 1.0000
10.500 1.3167 0.02219 0.01474 -0.0464 0.0181 1.0000
10.750 1.3311 0.02295 0.01557 -0.0448 0.0174 1.0000
11.000 1.3445 0.02379 0.01647 -0.0433 0.0166 1.0000
11.250 1.3570 0.02472 0.01746 -0.0417 0.0159 1.0000
11.500 1.3682 0.02577 0.01855 -0.0401 0.0153 1.0000
11.750 1.3763 0.02708 0.01991 -0.0384 0.0146 1.0000
12.000 1.3874 0.02819 0.02110 -0.0370 0.0142 1.0000
12.250 1.3971 0.02945 0.02244 -0.0356 0.0138 1.0000
12.500 1.4059 0.03082 0.02389 -0.0343 0.0134 1.0000
12.750 1.4138 0.03232 0.02548 -0.0330 0.0130 1.0000
13.000 1.4207 0.03394 0.02718 -0.0318 0.0126 1.0000
13.250 1.4265 0.03571 0.02902 -0.0308 0.0123 1.0000
13.500 1.4305 0.03772 0.03110 -0.0298 0.0120 1.0000
13.750 1.4313 0.04011 0.03357 -0.0288 0.0117 1.0000
14.000 1.4336 0.04243 0.03598 -0.0281 0.0115 1.0000
14.250 1.4363 0.04478 0.03844 -0.0275 0.0112 1.0000
14.500 1.4377 0.04736 0.04113 -0.0271 0.0110 1.0000
14.750 1.4379 0.05013 0.04400 -0.0268 0.0108 1.0000
15.000 1.4373 0.05313 0.04710 -0.0268 0.0105 1.0000
15.250 1.4357 0.05634 0.05042 -0.0269 0.0104 1.0000
15.500 1.4328 0.05980 0.05399 -0.0272 0.0102 1.0000
15.750 1.4292 0.06347 0.05776 -0.0277 0.0100 1.0000
16.000 1.4248 0.06735 0.06175 -0.0283 0.0099 1.0000
16.250 1.4194 0.07148 0.06598 -0.0292 0.0098 1.0000
16.500 1.4127 0.07585 0.07046 -0.0302 0.0097 1.0000
16.750 1.4052 0.08045 0.07515 -0.0314 0.0096 1.0000
17.000 1.3964 0.08534 0.08015 -0.0329 0.0095 1.0000
17.250 1.3866 0.09044 0.08536 -0.0344 0.0094 1.0000
17.500 1.3760 0.09571 0.09074 -0.0361 0.0093 1.0000
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