CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.41 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkk-il-1000000.txt Download as CSV file: xf-clarkk-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4838 0.09626 0.09444 -0.0410 1.0000 0.0273
-11.250 -0.4726 0.09477 0.09296 -0.0417 1.0000 0.0275
-11.000 -0.7590 0.03500 0.03221 -0.0830 0.9938 0.0315
-10.750 -0.7302 0.03483 0.03203 -0.0841 0.9917 0.0317
-10.500 -0.7003 0.03469 0.03188 -0.0853 0.9895 0.0319
-10.250 -0.6703 0.03431 0.03148 -0.0868 0.9876 0.0321
-10.000 -0.6386 0.03410 0.03127 -0.0883 0.9861 0.0324
-9.750 -0.6062 0.03397 0.03115 -0.0899 0.9849 0.0327
-9.500 -0.5761 0.03323 0.03035 -0.0916 0.9833 0.0333
-9.250 -0.5559 0.03112 0.02805 -0.0924 0.9780 0.0342
-9.000 -0.5453 0.02610 0.02233 -0.0929 0.9713 0.0365
-8.750 -0.5210 0.02541 0.02162 -0.0930 0.9658 0.0369
-8.500 -0.4958 0.02505 0.02127 -0.0928 0.9598 0.0372
-8.250 -0.4699 0.02472 0.02092 -0.0928 0.9545 0.0376
-8.000 -0.4469 0.02422 0.02039 -0.0923 0.9467 0.0380
-7.750 -0.4231 0.02355 0.01962 -0.0919 0.9400 0.0386
-7.500 -0.4004 0.02277 0.01873 -0.0913 0.9315 0.0395
-7.250 -0.3780 0.02154 0.01728 -0.0906 0.9240 0.0403
-7.000 -0.3550 0.02044 0.01596 -0.0900 0.9154 0.0409
-6.750 -0.3317 0.01974 0.01493 -0.0893 0.9076 0.0421
-6.500 -0.3085 0.01816 0.01328 -0.0890 0.8993 0.0428
-6.250 -0.2824 0.01771 0.01283 -0.0889 0.8919 0.0433
-6.000 -0.2563 0.01721 0.01231 -0.0887 0.8836 0.0439
-5.500 -0.2045 0.01585 0.01075 -0.0881 0.8675 0.0448
-5.000 -0.1517 0.01470 0.00938 -0.0876 0.8511 0.0459
-4.750 -0.1252 0.01408 0.00864 -0.0873 0.8431 0.0461
-4.500 -0.0983 0.01345 0.00793 -0.0871 0.8347 0.0463
-4.250 -0.0714 0.01292 0.00729 -0.0868 0.8267 0.0465
-4.000 -0.0441 0.01243 0.00675 -0.0866 0.8181 0.0468
-3.750 -0.0170 0.01203 0.00627 -0.0864 0.8100 0.0472
-3.500 0.0106 0.01171 0.00590 -0.0863 0.8015 0.0476
-3.250 0.0382 0.01173 0.00583 -0.0861 0.7932 0.0481
-3.000 0.0656 0.01133 0.00538 -0.0859 0.7846 0.0487
-2.750 0.0923 0.01065 0.00468 -0.0857 0.7765 0.0489
-2.500 0.1192 0.01014 0.00416 -0.0855 0.7678 0.0492
-2.250 0.1460 0.00976 0.00377 -0.0853 0.7594 0.0496
-2.000 0.1730 0.00944 0.00346 -0.0851 0.7504 0.0500
-1.750 0.2001 0.00920 0.00320 -0.0848 0.7417 0.0504
-1.500 0.2273 0.00900 0.00298 -0.0846 0.7324 0.0509
-1.250 0.2546 0.00882 0.00279 -0.0845 0.7233 0.0515
-0.750 0.3088 0.00857 0.00248 -0.0840 0.6997 0.0531
-0.500 0.3359 0.00846 0.00234 -0.0838 0.6867 0.0537
-0.250 0.3631 0.00837 0.00221 -0.0835 0.6761 0.0543
0.000 0.3905 0.00829 0.00210 -0.0834 0.6653 0.0548
0.250 0.4180 0.00822 0.00201 -0.0832 0.6541 0.0553
0.500 0.4453 0.00817 0.00194 -0.0830 0.6429 0.0557
1.000 0.4997 0.00804 0.00173 -0.0826 0.6187 0.0571
1.250 0.5268 0.00799 0.00165 -0.0824 0.6052 0.0584
1.500 0.5540 0.00798 0.00161 -0.0822 0.5922 0.0601
1.750 0.5811 0.00800 0.00160 -0.0820 0.5791 0.0618
2.000 0.6080 0.00805 0.00160 -0.0818 0.5648 0.0631
2.500 0.6620 0.00817 0.00164 -0.0813 0.5358 0.0666
2.750 0.6890 0.00822 0.00167 -0.0811 0.5223 0.0718
3.000 0.7150 0.00802 0.00175 -0.0808 0.5085 0.2133
3.250 0.7378 0.00726 0.00191 -0.0804 0.4941 0.5799
3.500 0.7581 0.00650 0.00214 -0.0785 0.4797 0.9656
3.750 0.8086 0.00669 0.00226 -0.0836 0.4605 1.0000
4.000 0.8329 0.00686 0.00236 -0.0828 0.4447 1.0000
4.250 0.8569 0.00706 0.00248 -0.0820 0.4258 1.0000
4.500 0.8801 0.00732 0.00262 -0.0812 0.4007 1.0000
4.750 0.9037 0.00759 0.00278 -0.0803 0.3761 1.0000
5.000 0.9272 0.00788 0.00295 -0.0795 0.3515 1.0000
5.250 0.9506 0.00819 0.00314 -0.0787 0.3271 1.0000
5.500 0.9742 0.00850 0.00334 -0.0780 0.3052 1.0000
5.750 0.9976 0.00883 0.00356 -0.0772 0.2819 1.0000
6.000 1.0207 0.00920 0.00380 -0.0764 0.2588 1.0000
6.250 1.0445 0.00950 0.00403 -0.0757 0.2417 1.0000
6.500 1.0686 0.00980 0.00426 -0.0751 0.2278 1.0000
6.750 1.0923 0.01012 0.00451 -0.0744 0.2130 1.0000
7.000 1.1159 0.01044 0.00476 -0.0737 0.1996 1.0000
7.250 1.1396 0.01075 0.00502 -0.0731 0.1865 1.0000
7.500 1.1627 0.01110 0.00530 -0.0723 0.1709 1.0000
7.750 1.1849 0.01152 0.00562 -0.0715 0.1513 1.0000
8.000 1.2030 0.01222 0.00611 -0.0700 0.1169 1.0000
8.250 1.2141 0.01344 0.00697 -0.0675 0.0636 1.0000
8.500 1.2279 0.01442 0.00775 -0.0653 0.0359 1.0000
8.750 1.2471 0.01499 0.00828 -0.0640 0.0305 1.0000
9.000 1.2676 0.01543 0.00875 -0.0629 0.0282 1.0000
9.250 1.2861 0.01596 0.00927 -0.0614 0.0262 1.0000
9.500 1.3031 0.01649 0.00984 -0.0597 0.0247 1.0000
9.750 1.3213 0.01695 0.01033 -0.0582 0.0237 1.0000
10.000 1.3383 0.01747 0.01088 -0.0566 0.0227 1.0000
10.250 1.3533 0.01813 0.01156 -0.0548 0.0216 1.0000
10.500 1.3667 0.01888 0.01236 -0.0528 0.0206 1.0000
10.750 1.3835 0.01943 0.01295 -0.0513 0.0201 1.0000
11.000 1.3989 0.02007 0.01363 -0.0497 0.0194 1.0000
11.250 1.4136 0.02077 0.01438 -0.0481 0.0188 1.0000
11.500 1.4268 0.02158 0.01522 -0.0464 0.0182 1.0000
11.750 1.4362 0.02267 0.01635 -0.0444 0.0176 1.0000
12.000 1.4425 0.02400 0.01776 -0.0421 0.0171 1.0000
12.250 1.4560 0.02486 0.01868 -0.0408 0.0168 1.0000
12.500 1.4682 0.02584 0.01972 -0.0394 0.0164 1.0000
12.750 1.4795 0.02692 0.02085 -0.0380 0.0159 1.0000
13.000 1.4901 0.02809 0.02207 -0.0367 0.0155 1.0000
13.250 1.4996 0.02936 0.02340 -0.0354 0.0152 1.0000
13.500 1.5073 0.03084 0.02492 -0.0342 0.0148 1.0000
13.750 1.5112 0.03270 0.02686 -0.0328 0.0145 1.0000
14.000 1.5082 0.03525 0.02950 -0.0312 0.0141 1.0000
14.250 1.5070 0.03776 0.03210 -0.0300 0.0139 1.0000
14.500 1.5132 0.03962 0.03404 -0.0293 0.0138 1.0000
14.750 1.5175 0.04172 0.03622 -0.0286 0.0136 1.0000
15.000 1.5202 0.04406 0.03865 -0.0281 0.0134 1.0000
15.250 1.5219 0.04660 0.04128 -0.0276 0.0132 1.0000
15.500 1.5226 0.04931 0.04408 -0.0274 0.0130 1.0000
15.750 1.5221 0.05226 0.04711 -0.0272 0.0128 1.0000
16.000 1.5212 0.05536 0.05029 -0.0273 0.0126 1.0000
16.250 1.5191 0.05870 0.05372 -0.0275 0.0124 1.0000
16.500 1.5161 0.06222 0.05733 -0.0279 0.0123 1.0000
16.750 1.5124 0.06593 0.06112 -0.0285 0.0121 1.0000
17.000 1.5072 0.06994 0.06521 -0.0292 0.0120 1.0000
17.250 1.5004 0.07425 0.06961 -0.0302 0.0119 1.0000
17.500 1.4919 0.07883 0.07429 -0.0313 0.0117 1.0000
17.750 1.4805 0.08393 0.07948 -0.0326 0.0116 1.0000
18.000 1.4671 0.08939 0.08504 -0.0341 0.0114 1.0000
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