CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 200,000 Max Cl/Cd: 75.72 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkk-il-200000.txt Download as CSV file: xf-clarkk-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3855 0.11617 0.11219 -0.0337 1.0000 0.0605
-10.750 -0.3868 0.11253 0.10857 -0.0362 1.0000 0.0631
-10.500 -0.4237 0.10581 0.10196 -0.0473 1.0000 0.0649
-10.250 -0.4008 0.10305 0.09917 -0.0425 1.0000 0.0658
-10.000 -0.3886 0.10084 0.09697 -0.0411 1.0000 0.0667
-9.750 -0.3812 0.09840 0.09453 -0.0407 1.0000 0.0680
-9.500 -0.3784 0.09561 0.09178 -0.0411 1.0000 0.0697
-9.250 -0.3562 0.08435 0.08097 -0.0441 1.0000 0.0756
-9.000 -0.3429 0.08338 0.08002 -0.0399 1.0000 0.0766
-8.750 -0.3445 0.08209 0.07877 -0.0368 1.0000 0.0776
-8.500 -0.3528 0.08061 0.07734 -0.0341 1.0000 0.0787
-8.250 -0.4926 0.07921 0.07583 -0.0406 1.0000 0.0762
-8.000 -0.4923 0.07848 0.07514 -0.0365 1.0000 0.0770
-7.750 -0.4994 0.07709 0.07378 -0.0337 1.0000 0.0778
-7.500 -0.4962 0.06263 0.05883 -0.0559 0.9894 0.0872
-7.250 -0.4673 0.06133 0.05766 -0.0556 0.9868 0.0885
-7.000 -0.4415 0.05707 0.05303 -0.0630 0.9805 0.0983
-6.750 -0.4199 0.05352 0.04958 -0.0645 0.9757 0.1013
-6.500 -0.3879 0.05244 0.04853 -0.0660 0.9724 0.1054
-6.250 -0.3632 0.04866 0.04456 -0.0703 0.9665 0.1159
-5.750 -0.3032 0.04384 0.03941 -0.0770 0.9568 0.1419
-5.500 -0.2745 0.04299 0.03864 -0.0774 0.9515 0.1485
-5.250 -0.2458 0.04113 0.03672 -0.0792 0.9458 0.1613
-5.000 -0.2109 0.03920 0.03470 -0.0822 0.9427 0.1762
-4.750 -0.1732 0.03732 0.03275 -0.0854 0.9407 0.1926
-4.250 -0.1101 0.02218 0.01481 -0.0884 0.9273 0.0943
-4.000 -0.0704 0.02076 0.01309 -0.0904 0.9250 0.0910
-3.750 -0.0451 0.02001 0.01217 -0.0896 0.9163 0.0903
-3.500 -0.0091 0.01916 0.01117 -0.0908 0.9121 0.0890
-3.250 0.0283 0.01846 0.01035 -0.0922 0.9089 0.0880
-3.000 0.0532 0.01799 0.00983 -0.0913 0.8998 0.0876
-2.750 0.0866 0.01731 0.00911 -0.0920 0.8950 0.0874
-2.500 0.1157 0.01669 0.00850 -0.0920 0.8885 0.0876
-2.250 0.1434 0.01602 0.00788 -0.0917 0.8810 0.0887
-2.000 0.1750 0.01538 0.00727 -0.0921 0.8763 0.0900
-1.750 0.1990 0.01504 0.00697 -0.0911 0.8665 0.0905
-1.500 0.2290 0.01457 0.00650 -0.0911 0.8606 0.0912
-1.250 0.2538 0.01431 0.00625 -0.0903 0.8510 0.0921
-1.000 0.2832 0.01396 0.00587 -0.0902 0.8444 0.0934
-0.750 0.3086 0.01378 0.00568 -0.0894 0.8346 0.0949
-0.500 0.3380 0.01351 0.00536 -0.0893 0.8276 0.0970
-0.250 0.3633 0.01337 0.00522 -0.0885 0.8170 0.1007
0.000 0.3918 0.01312 0.00498 -0.0882 0.8090 0.1075
0.250 0.4169 0.01274 0.00491 -0.0876 0.7984 0.1781
0.500 0.4430 0.01247 0.00486 -0.0870 0.7884 0.2535
0.750 0.4691 0.01198 0.00475 -0.0865 0.7788 0.3762
1.000 0.4881 0.01118 0.00480 -0.0846 0.7663 0.6249
1.250 0.5245 0.01049 0.00488 -0.0848 0.7543 0.9340
1.500 0.5814 0.01040 0.00470 -0.0905 0.7421 1.0000
1.750 0.6063 0.01046 0.00466 -0.0897 0.7304 1.0000
2.000 0.6304 0.01054 0.00467 -0.0887 0.7177 1.0000
2.250 0.6550 0.01063 0.00467 -0.0878 0.7055 1.0000
2.500 0.6802 0.01072 0.00467 -0.0870 0.6935 1.0000
2.750 0.7051 0.01081 0.00468 -0.0862 0.6808 1.0000
3.000 0.7292 0.01092 0.00475 -0.0853 0.6671 1.0000
3.250 0.7536 0.01104 0.00482 -0.0844 0.6531 1.0000
3.500 0.7781 0.01117 0.00489 -0.0836 0.6389 1.0000
3.750 0.8027 0.01131 0.00497 -0.0827 0.6246 1.0000
4.000 0.8270 0.01145 0.00506 -0.0819 0.6095 1.0000
4.250 0.8511 0.01162 0.00518 -0.0810 0.5934 1.0000
4.500 0.8750 0.01180 0.00531 -0.0800 0.5766 1.0000
4.750 0.8988 0.01201 0.00546 -0.0791 0.5595 1.0000
5.000 0.9221 0.01223 0.00564 -0.0781 0.5412 1.0000
5.250 0.9451 0.01249 0.00583 -0.0771 0.5219 1.0000
5.500 0.9677 0.01278 0.00604 -0.0760 0.5023 1.0000
5.750 0.9900 0.01309 0.00631 -0.0748 0.4813 1.0000
6.000 1.0115 0.01342 0.00659 -0.0736 0.4588 1.0000
6.250 1.0322 0.01382 0.00687 -0.0723 0.4353 1.0000
6.500 1.0524 0.01422 0.00721 -0.0709 0.4099 1.0000
6.750 1.0719 0.01469 0.00756 -0.0694 0.3858 1.0000
7.000 1.0914 0.01516 0.00795 -0.0679 0.3623 1.0000
7.250 1.1102 0.01569 0.00837 -0.0665 0.3414 1.0000
7.500 1.1294 0.01619 0.00881 -0.0651 0.3210 1.0000
7.750 1.1482 0.01669 0.00927 -0.0636 0.3015 1.0000
8.000 1.1667 0.01722 0.00975 -0.0622 0.2840 1.0000
8.250 1.1853 0.01774 0.01026 -0.0608 0.2686 1.0000
8.500 1.2036 0.01827 0.01078 -0.0593 0.2538 1.0000
8.750 1.2211 0.01881 0.01132 -0.0578 0.2388 1.0000
9.000 1.2374 0.01937 0.01189 -0.0561 0.2221 1.0000
9.250 1.2504 0.02001 0.01249 -0.0538 0.2021 1.0000
9.500 1.2604 0.02083 0.01321 -0.0513 0.1701 1.0000
9.750 1.2577 0.02262 0.01451 -0.0474 0.1001 1.0000
10.000 1.2543 0.02467 0.01626 -0.0436 0.0710 1.0000
10.250 1.2579 0.02625 0.01782 -0.0408 0.0618 1.0000
10.500 1.2616 0.02786 0.01945 -0.0383 0.0567 1.0000
10.750 1.2674 0.02936 0.02103 -0.0361 0.0530 1.0000
11.000 1.2676 0.03133 0.02302 -0.0338 0.0505 1.0000
11.250 1.2715 0.03312 0.02490 -0.0318 0.0486 1.0000
11.500 1.2768 0.03486 0.02673 -0.0302 0.0467 1.0000
11.750 1.2811 0.03675 0.02867 -0.0286 0.0449 1.0000
12.000 1.2832 0.03887 0.03081 -0.0271 0.0434 1.0000
12.250 1.2846 0.04118 0.03311 -0.0253 0.0421 1.0000
12.500 1.2919 0.04297 0.03503 -0.0241 0.0409 1.0000
12.750 1.2989 0.04484 0.03699 -0.0229 0.0399 1.0000
13.000 1.3064 0.04671 0.03894 -0.0217 0.0389 1.0000
13.250 1.3143 0.04857 0.04084 -0.0206 0.0379 1.0000
13.500 1.3236 0.05036 0.04263 -0.0194 0.0369 1.0000
13.750 1.3410 0.05200 0.04420 -0.0178 0.0356 1.0000
14.000 1.3452 0.05419 0.04659 -0.0169 0.0350 1.0000
14.250 1.3502 0.05645 0.04903 -0.0160 0.0343 1.0000
14.500 1.3562 0.05876 0.05149 -0.0151 0.0336 1.0000
14.750 1.3613 0.06121 0.05410 -0.0143 0.0331 1.0000
15.000 1.3653 0.06382 0.05686 -0.0136 0.0326 1.0000
15.250 1.3681 0.06658 0.05978 -0.0130 0.0322 1.0000
15.500 1.3699 0.06947 0.06283 -0.0125 0.0318 1.0000
15.750 1.3688 0.07266 0.06617 -0.0122 0.0315 1.0000
16.000 1.3667 0.07602 0.06967 -0.0121 0.0311 1.0000
16.250 1.3662 0.07935 0.07310 -0.0120 0.0307 1.0000
16.500 1.3661 0.08311 0.07698 -0.0118 0.0302 1.0000
16.750 1.3567 0.08809 0.08216 -0.0122 0.0300 1.0000
17.000 1.3387 0.09339 0.08768 -0.0139 0.0299 1.0000
17.250 1.3210 0.09902 0.09353 -0.0160 0.0299 1.0000
17.500 1.3028 0.10508 0.09981 -0.0187 0.0299 1.0000
17.750 1.2840 0.11162 0.10657 -0.0219 0.0299 1.0000
18.000 1.2659 0.11841 0.11356 -0.0254 0.0300 1.0000
18.250 1.2458 0.12583 0.12119 -0.0303 0.0301 1.0000
18.500 1.2119 0.13697 0.13267 -0.0389 0.0306 1.0000
18.750 1.0669 0.18250 0.17886 -0.0707 0.0359 1.0000
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Polar data table (+)
Polar graphs
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