CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 500,000 Max Cl/Cd: 102.73 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkk-il-500000.txt Download as CSV file: xf-clarkk-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4311 0.09364 0.09115 -0.0488 1.0000 0.0418
-10.250 -0.4287 0.09033 0.08786 -0.0478 1.0000 0.0422
-10.000 -0.4206 0.08862 0.08616 -0.0469 1.0000 0.0424
-9.750 -0.4140 0.08684 0.08440 -0.0463 1.0000 0.0428
-9.500 -0.4106 0.08489 0.08248 -0.0458 1.0000 0.0432
-9.250 -0.4124 0.08269 0.08031 -0.0452 1.0000 0.0437
-9.000 -0.4233 0.08046 0.07813 -0.0436 1.0000 0.0442
-8.750 -0.4893 0.05452 0.05148 -0.0789 0.9852 0.0483
-8.500 -0.4800 0.04547 0.04221 -0.0842 0.9825 0.0490
-8.250 -0.4556 0.04335 0.04017 -0.0852 0.9784 0.0496
-8.000 -0.4270 0.04169 0.03855 -0.0871 0.9756 0.0503
-7.750 -0.3988 0.03939 0.03615 -0.0899 0.9731 0.0515
-7.500 -0.3736 0.03813 0.03413 -0.0924 0.9679 0.0558
-7.250 -0.3619 0.03231 0.02790 -0.0933 0.9603 0.0569
-7.000 -0.3331 0.02983 0.02552 -0.0947 0.9571 0.0578
-6.750 -0.3099 0.02827 0.02393 -0.0947 0.9505 0.0588
-6.500 -0.2855 0.02684 0.02239 -0.0948 0.9440 0.0601
-6.250 -0.2613 0.02583 0.02115 -0.0945 0.9376 0.0626
-6.000 -0.2424 0.02433 0.01914 -0.0934 0.9288 0.0661
-5.750 -0.2175 0.02250 0.01737 -0.0934 0.9228 0.0674
-5.500 -0.1940 0.02139 0.01621 -0.0929 0.9145 0.0690
-5.250 -0.1683 0.02058 0.01525 -0.0926 0.9082 0.0714
-5.000 -0.1461 0.01954 0.01391 -0.0918 0.8991 0.0771
-4.750 -0.1201 0.01830 0.01269 -0.0917 0.8926 0.0791
-4.500 -0.0949 0.01762 0.01195 -0.0912 0.8839 0.0822
-4.250 -0.0702 0.01658 0.01075 -0.0910 0.8768 0.0903
-4.000 -0.0442 0.01593 0.01009 -0.0906 0.8682 0.0941
-3.750 -0.0167 0.01571 0.00973 -0.0902 0.8608 0.0975
-3.500 0.0156 0.01477 0.00828 -0.0889 0.8528 0.0638
-3.250 0.0427 0.01399 0.00742 -0.0886 0.8451 0.0634
-3.000 0.0697 0.01346 0.00683 -0.0883 0.8367 0.0635
-2.750 0.0969 0.01286 0.00618 -0.0880 0.8289 0.0631
-2.500 0.1239 0.01238 0.00566 -0.0877 0.8204 0.0629
-2.250 0.1511 0.01197 0.00521 -0.0873 0.8123 0.0629
-2.000 0.1780 0.01160 0.00483 -0.0870 0.8035 0.0630
-1.750 0.2051 0.01129 0.00447 -0.0867 0.7953 0.0631
-1.500 0.2320 0.01100 0.00418 -0.0864 0.7861 0.0634
-1.250 0.2592 0.01081 0.00394 -0.0861 0.7778 0.0640
-1.000 0.2863 0.01064 0.00377 -0.0858 0.7679 0.0646
-0.750 0.3132 0.01043 0.00353 -0.0855 0.7590 0.0649
-0.500 0.3395 0.01009 0.00319 -0.0851 0.7489 0.0655
-0.250 0.3659 0.00985 0.00293 -0.0847 0.7383 0.0662
0.000 0.3923 0.00967 0.00271 -0.0843 0.7263 0.0670
0.250 0.4189 0.00954 0.00255 -0.0839 0.7135 0.0680
0.500 0.4458 0.00943 0.00243 -0.0836 0.7020 0.0691
0.750 0.4729 0.00936 0.00234 -0.0833 0.6916 0.0706
1.000 0.4999 0.00933 0.00226 -0.0830 0.6806 0.0726
1.250 0.5270 0.00930 0.00221 -0.0828 0.6687 0.0743
1.500 0.5541 0.00929 0.00217 -0.0825 0.6574 0.0763
1.750 0.5809 0.00930 0.00214 -0.0822 0.6456 0.0806
2.000 0.6074 0.00923 0.00214 -0.0818 0.6325 0.1074
2.250 0.6326 0.00887 0.00221 -0.0815 0.6193 0.2731
2.500 0.6537 0.00798 0.00234 -0.0806 0.6069 0.6329
2.750 0.6985 0.00735 0.00256 -0.0836 0.5917 0.9937
3.000 0.7313 0.00749 0.00261 -0.0847 0.5761 1.0000
3.250 0.7553 0.00764 0.00269 -0.0839 0.5614 1.0000
3.500 0.7794 0.00780 0.00278 -0.0831 0.5470 1.0000
3.750 0.8035 0.00797 0.00288 -0.0822 0.5320 1.0000
4.000 0.8275 0.00816 0.00300 -0.0814 0.5160 1.0000
4.250 0.8516 0.00835 0.00313 -0.0806 0.4994 1.0000
4.500 0.8758 0.00855 0.00327 -0.0799 0.4830 1.0000
4.750 0.8999 0.00876 0.00343 -0.0791 0.4657 1.0000
5.000 0.9236 0.00900 0.00360 -0.0783 0.4448 1.0000
5.250 0.9462 0.00932 0.00379 -0.0773 0.4202 1.0000
5.500 0.9691 0.00963 0.00400 -0.0764 0.3938 1.0000
5.750 0.9915 0.00999 0.00425 -0.0754 0.3686 1.0000
6.000 1.0138 0.01036 0.00451 -0.0745 0.3439 1.0000
6.250 1.0359 0.01076 0.00479 -0.0735 0.3197 1.0000
6.500 1.0575 0.01119 0.00510 -0.0725 0.2954 1.0000
6.750 1.0794 0.01161 0.00542 -0.0715 0.2747 1.0000
7.000 1.1017 0.01199 0.00574 -0.0707 0.2576 1.0000
7.250 1.1239 0.01238 0.00607 -0.0698 0.2417 1.0000
7.500 1.1458 0.01278 0.00641 -0.0688 0.2264 1.0000
7.750 1.1676 0.01319 0.00676 -0.0679 0.2127 1.0000
8.000 1.1891 0.01360 0.00713 -0.0669 0.1986 1.0000
8.250 1.2102 0.01404 0.00752 -0.0659 0.1818 1.0000
8.500 1.2289 0.01463 0.00797 -0.0646 0.1564 1.0000
8.750 1.2401 0.01572 0.00872 -0.0622 0.1037 1.0000
9.000 1.2424 0.01730 0.00991 -0.0584 0.0525 1.0000
9.250 1.2536 0.01823 0.01077 -0.0559 0.0412 1.0000
9.500 1.2668 0.01904 0.01157 -0.0537 0.0369 1.0000
9.750 1.2807 0.01981 0.01239 -0.0518 0.0342 1.0000
10.000 1.2944 0.02059 0.01321 -0.0499 0.0322 1.0000
10.250 1.3039 0.02166 0.01431 -0.0475 0.0304 1.0000
10.500 1.3151 0.02263 0.01536 -0.0455 0.0293 1.0000
10.750 1.3271 0.02357 0.01637 -0.0437 0.0283 1.0000
11.000 1.3375 0.02464 0.01750 -0.0418 0.0273 1.0000
11.250 1.3460 0.02588 0.01880 -0.0399 0.0264 1.0000
11.500 1.3490 0.02757 0.02053 -0.0377 0.0255 1.0000
11.750 1.3523 0.02932 0.02237 -0.0356 0.0248 1.0000
12.000 1.3619 0.03063 0.02377 -0.0343 0.0242 1.0000
12.250 1.3693 0.03217 0.02539 -0.0329 0.0236 1.0000
12.500 1.3752 0.03388 0.02718 -0.0316 0.0230 1.0000
12.750 1.3800 0.03575 0.02911 -0.0303 0.0225 1.0000
13.000 1.3835 0.03778 0.03121 -0.0292 0.0220 1.0000
13.250 1.3848 0.04009 0.03359 -0.0281 0.0216 1.0000
13.500 1.3822 0.04282 0.03638 -0.0269 0.0211 1.0000
13.750 1.3780 0.04576 0.03939 -0.0257 0.0208 1.0000
14.000 1.3830 0.04790 0.04164 -0.0252 0.0205 1.0000
14.250 1.3867 0.05023 0.04407 -0.0247 0.0201 1.0000
14.500 1.3894 0.05272 0.04666 -0.0243 0.0197 1.0000
14.750 1.3917 0.05532 0.04935 -0.0241 0.0193 1.0000
15.000 1.3932 0.05805 0.05218 -0.0239 0.0189 1.0000
15.250 1.3943 0.06089 0.05510 -0.0239 0.0186 1.0000
15.500 1.3950 0.06383 0.05811 -0.0240 0.0183 1.0000
15.750 1.3954 0.06684 0.06118 -0.0241 0.0180 1.0000
16.000 1.3953 0.06986 0.06426 -0.0241 0.0178 1.0000
16.250 1.3952 0.07280 0.06724 -0.0240 0.0175 1.0000
16.500 1.3955 0.07532 0.06980 -0.0227 0.0171 1.0000
16.750 1.3937 0.07894 0.07357 -0.0236 0.0170 1.0000
17.000 1.3912 0.08268 0.07744 -0.0244 0.0168 1.0000
17.250 1.3883 0.08651 0.08141 -0.0254 0.0167 1.0000
17.500 1.3848 0.09047 0.08550 -0.0264 0.0165 1.0000
17.750 1.3806 0.09460 0.08977 -0.0276 0.0163 1.0000
18.000 1.3759 0.09886 0.09416 -0.0289 0.0161 1.0000
18.250 1.3705 0.10329 0.09871 -0.0305 0.0159 1.0000
18.500 1.3647 0.10786 0.10341 -0.0322 0.0158 1.0000
18.750 1.3588 0.11256 0.10823 -0.0342 0.0156 1.0000
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