CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.44 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkk-il-1000000-n5.txt Download as CSV file: xf-clarkk-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0913 0.04829 0.04566 -0.0822 1.0000 0.0143
-15.750 -1.1295 0.03949 0.03656 -0.0907 1.0000 0.0142
-15.500 -1.1513 0.03531 0.03217 -0.0915 1.0000 0.0144
-15.250 -1.1659 0.03250 0.02919 -0.0893 1.0000 0.0148
-15.000 -1.1696 0.03002 0.02655 -0.0874 1.0000 0.0154
-14.750 -1.1686 0.02800 0.02439 -0.0853 1.0000 0.0160
-14.500 -1.1666 0.02619 0.02245 -0.0828 1.0000 0.0167
-14.250 -1.1634 0.02458 0.02074 -0.0801 1.0000 0.0177
-14.000 -1.1437 0.02300 0.01906 -0.0804 0.9982 0.0192
-13.750 -1.1195 0.02175 0.01775 -0.0812 0.9962 0.0211
-13.500 -1.0924 0.02088 0.01682 -0.0822 0.9945 0.0233
-13.250 -1.0607 0.02094 0.01696 -0.0831 0.9932 0.0252
-13.000 -1.0331 0.02048 0.01647 -0.0837 0.9908 0.0269
-12.750 -1.0043 0.02004 0.01598 -0.0844 0.9886 0.0280
-12.500 -0.9705 0.02058 0.01659 -0.0853 0.9870 0.0287
-12.250 -0.9373 0.02099 0.01703 -0.0862 0.9853 0.0294
-12.000 -0.9088 0.02057 0.01656 -0.0868 0.9826 0.0305
-11.750 -0.8859 0.01927 0.01510 -0.0869 0.9782 0.0317
-11.500 -0.8602 0.01818 0.01384 -0.0874 0.9748 0.0325
-11.250 -0.8324 0.01797 0.01359 -0.0877 0.9707 0.0329
-11.000 -0.8032 0.01810 0.01373 -0.0879 0.9663 0.0333
-10.750 -0.7734 0.01821 0.01382 -0.0883 0.9624 0.0336
-10.500 -0.7462 0.01830 0.01390 -0.0882 0.9565 0.0339
-10.250 -0.7182 0.01838 0.01396 -0.0882 0.9512 0.0342
-10.000 -0.6914 0.01842 0.01397 -0.0881 0.9451 0.0345
-9.750 -0.6649 0.01835 0.01385 -0.0879 0.9387 0.0349
-9.500 -0.6390 0.01817 0.01361 -0.0877 0.9322 0.0354
-9.250 -0.6134 0.01786 0.01322 -0.0874 0.9251 0.0360
-9.000 -0.5884 0.01733 0.01259 -0.0871 0.9180 0.0368
-8.750 -0.5633 0.01682 0.01196 -0.0868 0.9103 0.0374
-8.500 -0.5379 0.01634 0.01137 -0.0865 0.9030 0.0378
-8.250 -0.5121 0.01595 0.01088 -0.0862 0.8946 0.0381
-8.000 -0.4860 0.01564 0.01048 -0.0860 0.8867 0.0383
-7.750 -0.4616 0.01476 0.00948 -0.0856 0.8776 0.0387
-7.500 -0.4359 0.01423 0.00888 -0.0854 0.8689 0.0390
-7.250 -0.4098 0.01385 0.00843 -0.0851 0.8594 0.0392
-7.000 -0.3832 0.01355 0.00807 -0.0850 0.8504 0.0394
-6.500 -0.3296 0.01307 0.00748 -0.0846 0.8326 0.0399
-6.250 -0.3030 0.01276 0.00710 -0.0844 0.8240 0.0402
-6.000 -0.2760 0.01244 0.00672 -0.0843 0.8153 0.0404
-5.750 -0.2493 0.01214 0.00635 -0.0841 0.8068 0.0406
-5.500 -0.2222 0.01183 0.00599 -0.0840 0.7982 0.0409
-5.250 -0.1954 0.01154 0.00564 -0.0838 0.7897 0.0411
-5.000 -0.1683 0.01124 0.00530 -0.0836 0.7813 0.0414
-4.750 -0.1413 0.01097 0.00498 -0.0835 0.7730 0.0417
-4.500 -0.1141 0.01071 0.00467 -0.0833 0.7646 0.0420
-4.250 -0.0871 0.01047 0.00438 -0.0832 0.7565 0.0424
-4.000 -0.0597 0.01024 0.00411 -0.0830 0.7481 0.0427
-3.750 -0.0324 0.01006 0.00390 -0.0829 0.7401 0.0432
-3.500 -0.0049 0.00990 0.00370 -0.0828 0.7316 0.0436
-3.250 0.0224 0.00972 0.00348 -0.0826 0.7236 0.0439
-3.000 0.0499 0.00956 0.00328 -0.0825 0.7148 0.0442
-2.750 0.0773 0.00942 0.00311 -0.0824 0.7065 0.0444
-2.500 0.1048 0.00929 0.00295 -0.0823 0.6974 0.0446
-2.250 0.1323 0.00917 0.00280 -0.0822 0.6886 0.0448
-2.000 0.1598 0.00907 0.00266 -0.0821 0.6787 0.0449
-1.750 0.1872 0.00893 0.00249 -0.0820 0.6688 0.0451
-1.500 0.2140 0.00873 0.00225 -0.0817 0.6581 0.0456
-1.250 0.2413 0.00860 0.00209 -0.0816 0.6464 0.0460
-1.000 0.2684 0.00853 0.00197 -0.0814 0.6315 0.0464
-0.750 0.2951 0.00852 0.00189 -0.0811 0.6110 0.0468
-0.500 0.3218 0.00852 0.00182 -0.0809 0.5906 0.0472
-0.250 0.3490 0.00851 0.00176 -0.0807 0.5756 0.0477
0.000 0.3763 0.00850 0.00172 -0.0805 0.5622 0.0482
0.250 0.4036 0.00851 0.00168 -0.0804 0.5479 0.0488
0.500 0.4309 0.00852 0.00166 -0.0802 0.5349 0.0496
0.750 0.4582 0.00854 0.00165 -0.0801 0.5231 0.0504
1.000 0.4853 0.00858 0.00165 -0.0799 0.5097 0.0510
1.250 0.5124 0.00862 0.00165 -0.0798 0.4952 0.0516
1.500 0.5398 0.00866 0.00167 -0.0796 0.4828 0.0520
1.750 0.5670 0.00871 0.00169 -0.0795 0.4708 0.0524
2.000 0.5940 0.00877 0.00172 -0.0793 0.4569 0.0528
2.250 0.6207 0.00884 0.00174 -0.0791 0.4411 0.0539
2.500 0.6475 0.00893 0.00178 -0.0789 0.4257 0.0550
2.750 0.6742 0.00903 0.00184 -0.0787 0.4111 0.0562
3.000 0.7008 0.00914 0.00191 -0.0784 0.3955 0.0575
3.250 0.7271 0.00928 0.00200 -0.0782 0.3777 0.0591
3.500 0.7533 0.00944 0.00210 -0.0779 0.3590 0.0610
3.750 0.7794 0.00959 0.00222 -0.0776 0.3425 0.0670
4.000 0.8050 0.00954 0.00236 -0.0773 0.3273 0.1960
4.250 0.8279 0.00884 0.00260 -0.0770 0.3130 0.5941
4.500 0.8480 0.00818 0.00287 -0.0752 0.2983 0.9670
4.750 0.8867 0.00849 0.00307 -0.0778 0.2747 1.0000
5.000 0.9102 0.00879 0.00326 -0.0770 0.2537 1.0000
5.250 0.9347 0.00904 0.00344 -0.0764 0.2398 1.0000
5.500 0.9593 0.00928 0.00362 -0.0759 0.2276 1.0000
5.750 0.9834 0.00956 0.00383 -0.0752 0.2126 1.0000
6.000 1.0074 0.00986 0.00405 -0.0746 0.1980 1.0000
6.250 1.0313 0.01016 0.00428 -0.0740 0.1832 1.0000
6.500 1.0551 0.01047 0.00452 -0.0733 0.1694 1.0000
6.750 1.0783 0.01083 0.00479 -0.0726 0.1525 1.0000
7.000 1.1006 0.01125 0.00510 -0.0717 0.1326 1.0000
7.250 1.1203 0.01186 0.00554 -0.0705 0.1031 1.0000
7.500 1.1380 0.01263 0.00610 -0.0690 0.0695 1.0000
7.750 1.1534 0.01356 0.00680 -0.0671 0.0347 1.0000
8.000 1.1748 0.01400 0.00722 -0.0661 0.0277 1.0000
8.250 1.1963 0.01442 0.00762 -0.0651 0.0241 1.0000
8.500 1.2183 0.01479 0.00799 -0.0643 0.0220 1.0000
8.750 1.2396 0.01518 0.00839 -0.0633 0.0202 1.0000
9.000 1.2599 0.01563 0.00885 -0.0622 0.0184 1.0000
9.250 1.2806 0.01601 0.00924 -0.0611 0.0176 1.0000
9.500 1.2995 0.01641 0.00966 -0.0597 0.0165 1.0000
9.750 1.3174 0.01688 0.01014 -0.0582 0.0155 1.0000
10.000 1.3346 0.01739 0.01067 -0.0567 0.0145 1.0000
10.250 1.3526 0.01785 0.01116 -0.0553 0.0139 1.0000
10.500 1.3698 0.01836 0.01170 -0.0538 0.0133 1.0000
10.750 1.3862 0.01893 0.01229 -0.0523 0.0127 1.0000
11.000 1.4017 0.01955 0.01294 -0.0507 0.0122 1.0000
11.250 1.4160 0.02026 0.01368 -0.0491 0.0116 1.0000
11.500 1.4315 0.02091 0.01438 -0.0476 0.0113 1.0000
11.750 1.4463 0.02161 0.01512 -0.0461 0.0109 1.0000
12.000 1.4605 0.02237 0.01592 -0.0447 0.0105 1.0000
12.250 1.4737 0.02321 0.01680 -0.0432 0.0101 1.0000
12.500 1.4861 0.02414 0.01777 -0.0417 0.0097 1.0000
12.750 1.4971 0.02519 0.01886 -0.0402 0.0094 1.0000
13.000 1.5071 0.02635 0.02007 -0.0387 0.0091 1.0000
13.250 1.5181 0.02746 0.02125 -0.0374 0.0089 1.0000
13.500 1.5282 0.02867 0.02252 -0.0361 0.0087 1.0000
13.750 1.5375 0.02999 0.02391 -0.0349 0.0085 1.0000
14.000 1.5460 0.03142 0.02540 -0.0337 0.0083 1.0000
14.250 1.5535 0.03296 0.02701 -0.0326 0.0081 1.0000
14.500 1.5600 0.03464 0.02876 -0.0316 0.0080 1.0000
14.750 1.5657 0.03645 0.03064 -0.0306 0.0078 1.0000
15.000 1.5702 0.03843 0.03268 -0.0298 0.0076 1.0000
15.250 1.5732 0.04060 0.03492 -0.0290 0.0075 1.0000
15.500 1.5744 0.04304 0.03744 -0.0283 0.0073 1.0000
15.750 1.5731 0.04585 0.04034 -0.0278 0.0071 1.0000
16.000 1.5738 0.04852 0.04309 -0.0275 0.0070 1.0000
16.250 1.5741 0.05134 0.04600 -0.0274 0.0069 1.0000
16.500 1.5732 0.05439 0.04914 -0.0274 0.0068 1.0000
16.750 1.5705 0.05776 0.05261 -0.0276 0.0068 1.0000
17.000 1.5668 0.06132 0.05627 -0.0280 0.0067 1.0000
17.250 1.5614 0.06523 0.06028 -0.0286 0.0066 1.0000
17.500 1.5550 0.06938 0.06454 -0.0294 0.0065 1.0000
17.750 1.5473 0.07379 0.06906 -0.0304 0.0064 1.0000
18.000 1.5381 0.07849 0.07386 -0.0315 0.0064 1.0000
18.250 1.5275 0.08349 0.07897 -0.0329 0.0063 1.0000
18.500 1.5157 0.08878 0.08438 -0.0345 0.0063 1.0000
18.750 1.5030 0.09428 0.08999 -0.0362 0.0062 1.0000
19.000 1.4896 0.09996 0.09578 -0.0382 0.0062 1.0000
19.250 1.4751 0.10594 0.10188 -0.0404 0.0061 1.0000
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Polar data table (+)
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