CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 500,000 Max Cl/Cd: 93.54 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkz-il-500000-n5.txt Download as CSV file: xf-clarkz-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Z 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3591 0.09380 0.09132 -0.0432 1.0000 0.0226
-9.750 -0.3630 0.08846 0.08599 -0.0463 0.9978 0.0229
-9.500 -0.4985 0.03697 0.03381 -0.0958 0.9601 0.0243
-9.250 -0.4927 0.03194 0.02836 -0.0976 0.9495 0.0245
-9.000 -0.4750 0.02956 0.02573 -0.0982 0.9422 0.0248
-8.750 -0.4572 0.02763 0.02358 -0.0981 0.9333 0.0252
-8.500 -0.4395 0.02529 0.02092 -0.0980 0.9255 0.0254
-8.250 -0.4208 0.02331 0.01864 -0.0975 0.9168 0.0257
-8.000 -0.3998 0.02168 0.01673 -0.0971 0.9091 0.0260
-7.750 -0.3778 0.02032 0.01512 -0.0966 0.9007 0.0262
-7.500 -0.3544 0.01915 0.01372 -0.0962 0.8932 0.0265
-7.250 -0.3306 0.01815 0.01251 -0.0957 0.8847 0.0267
-7.000 -0.3058 0.01728 0.01145 -0.0953 0.8770 0.0270
-6.750 -0.2807 0.01651 0.01051 -0.0949 0.8684 0.0272
-6.500 -0.2551 0.01585 0.00969 -0.0945 0.8606 0.0275
-6.250 -0.2291 0.01532 0.00902 -0.0942 0.8516 0.0277
-6.000 -0.2033 0.01467 0.00824 -0.0938 0.8433 0.0280
-5.750 -0.1776 0.01404 0.00753 -0.0935 0.8342 0.0285
-5.500 -0.1514 0.01357 0.00699 -0.0931 0.8255 0.0288
-5.250 -0.1250 0.01316 0.00650 -0.0928 0.8159 0.0291
-5.000 -0.0984 0.01278 0.00607 -0.0925 0.8063 0.0294
-4.750 -0.0719 0.01245 0.00565 -0.0921 0.7967 0.0297
-4.500 -0.0452 0.01212 0.00526 -0.0918 0.7864 0.0301
-4.250 -0.0185 0.01182 0.00489 -0.0915 0.7769 0.0305
-4.000 0.0083 0.01154 0.00455 -0.0912 0.7668 0.0309
-3.750 0.0352 0.01128 0.00423 -0.0909 0.7571 0.0314
-3.500 0.0620 0.01106 0.00394 -0.0906 0.7472 0.0318
-3.250 0.0890 0.01085 0.00367 -0.0903 0.7368 0.0323
-3.000 0.1161 0.01068 0.00344 -0.0900 0.7267 0.0327
-2.750 0.1426 0.01043 0.00315 -0.0897 0.7161 0.0336
-2.500 0.1698 0.01026 0.00297 -0.0894 0.7060 0.0346
-2.250 0.1968 0.01014 0.00280 -0.0892 0.6961 0.0356
-2.000 0.2241 0.01002 0.00264 -0.0889 0.6858 0.0365
-1.750 0.2514 0.00992 0.00250 -0.0887 0.6760 0.0376
-1.500 0.2785 0.00983 0.00236 -0.0884 0.6658 0.0389
-1.250 0.3058 0.00973 0.00225 -0.0882 0.6555 0.0410
-1.000 0.3329 0.00967 0.00215 -0.0879 0.6455 0.0438
-0.750 0.3601 0.00960 0.00208 -0.0877 0.6346 0.0496
-0.500 0.3871 0.00950 0.00202 -0.0875 0.6238 0.0651
-0.250 0.4138 0.00941 0.00199 -0.0872 0.6132 0.0944
0.000 0.4408 0.00934 0.00198 -0.0870 0.6017 0.1210
0.250 0.4677 0.00929 0.00197 -0.0867 0.5900 0.1484
0.500 0.4943 0.00924 0.00198 -0.0865 0.5784 0.1853
0.750 0.5202 0.00905 0.00200 -0.0862 0.5663 0.2723
1.000 0.5431 0.00837 0.00207 -0.0856 0.5539 0.5427
1.250 0.5604 0.00765 0.00221 -0.0832 0.5421 0.8216
1.500 0.5955 0.00759 0.00234 -0.0842 0.5288 0.9585
1.750 0.6464 0.00774 0.00239 -0.0892 0.5126 0.9969
2.000 0.6754 0.00789 0.00245 -0.0894 0.4985 1.0000
2.250 0.6995 0.00804 0.00251 -0.0886 0.4853 1.0000
2.500 0.7237 0.00819 0.00258 -0.0879 0.4719 1.0000
2.750 0.7480 0.00836 0.00267 -0.0871 0.4589 1.0000
3.000 0.7721 0.00855 0.00277 -0.0863 0.4443 1.0000
3.250 0.7961 0.00876 0.00289 -0.0855 0.4284 1.0000
3.500 0.8201 0.00897 0.00302 -0.0848 0.4127 1.0000
3.750 0.8444 0.00919 0.00315 -0.0841 0.3979 1.0000
4.000 0.8686 0.00942 0.00330 -0.0834 0.3835 1.0000
4.500 0.9176 0.00987 0.00361 -0.0821 0.3567 1.0000
4.750 0.9420 0.01011 0.00379 -0.0815 0.3424 1.0000
5.000 0.9660 0.01037 0.00397 -0.0808 0.3273 1.0000
5.250 0.9905 0.01061 0.00417 -0.0803 0.3164 1.0000
5.500 1.0148 0.01087 0.00437 -0.0797 0.3057 1.0000
5.750 1.0392 0.01111 0.00458 -0.0791 0.2940 1.0000
6.000 1.0632 0.01138 0.00480 -0.0784 0.2817 1.0000
6.250 1.0868 0.01167 0.00504 -0.0778 0.2694 1.0000
6.500 1.1102 0.01198 0.00530 -0.0771 0.2567 1.0000
7.000 1.1555 0.01269 0.00588 -0.0755 0.2265 1.0000
7.250 1.1770 0.01312 0.00623 -0.0745 0.2074 1.0000
7.500 1.1972 0.01362 0.00662 -0.0734 0.1865 1.0000
7.750 1.2167 0.01416 0.00705 -0.0722 0.1672 1.0000
8.000 1.2360 0.01470 0.00751 -0.0709 0.1493 1.0000
8.250 1.2548 0.01525 0.00799 -0.0696 0.1332 1.0000
8.500 1.2731 0.01580 0.00847 -0.0682 0.1203 1.0000
8.750 1.2901 0.01635 0.00897 -0.0666 0.1101 1.0000
9.000 1.3065 0.01691 0.00950 -0.0649 0.1017 1.0000
9.250 1.3235 0.01743 0.01001 -0.0633 0.0954 1.0000
9.500 1.3393 0.01804 0.01059 -0.0616 0.0898 1.0000
9.750 1.3564 0.01857 0.01115 -0.0601 0.0861 1.0000
10.000 1.3734 0.01911 0.01172 -0.0587 0.0832 1.0000
10.250 1.3891 0.01973 0.01236 -0.0572 0.0803 1.0000
10.500 1.4037 0.02043 0.01307 -0.0556 0.0775 1.0000
10.750 1.4197 0.02105 0.01374 -0.0542 0.0757 1.0000
11.000 1.4356 0.02169 0.01444 -0.0529 0.0735 1.0000
11.250 1.4503 0.02242 0.01521 -0.0515 0.0709 1.0000
11.500 1.4637 0.02325 0.01607 -0.0500 0.0686 1.0000
11.750 1.4759 0.02420 0.01704 -0.0485 0.0664 1.0000
12.000 1.4904 0.02499 0.01792 -0.0473 0.0650 1.0000
12.250 1.5039 0.02588 0.01886 -0.0461 0.0629 1.0000
12.500 1.5161 0.02689 0.01992 -0.0449 0.0604 1.0000
12.750 1.5261 0.02810 0.02114 -0.0435 0.0574 1.0000
13.000 1.5380 0.02919 0.02229 -0.0424 0.0549 1.0000
13.250 1.5483 0.03043 0.02358 -0.0413 0.0519 1.0000
13.500 1.5565 0.03190 0.02507 -0.0401 0.0489 1.0000
13.750 1.5654 0.03333 0.02657 -0.0391 0.0454 1.0000
14.000 1.5707 0.03511 0.02836 -0.0380 0.0400 1.0000
14.250 1.5713 0.03739 0.03062 -0.0369 0.0313 1.0000
14.500 1.5641 0.04050 0.03369 -0.0356 0.0222 1.0000
14.750 1.5604 0.04340 0.03663 -0.0347 0.0191 1.0000
15.000 1.5590 0.04618 0.03950 -0.0341 0.0176 1.0000
15.250 1.5570 0.04912 0.04252 -0.0336 0.0165 1.0000
15.500 1.5546 0.05221 0.04569 -0.0333 0.0156 1.0000
15.750 1.5539 0.05520 0.04879 -0.0332 0.0150 1.0000
16.000 1.5518 0.05843 0.05212 -0.0333 0.0146 1.0000
16.250 1.5483 0.06191 0.05571 -0.0335 0.0141 1.0000
16.500 1.5435 0.06565 0.05956 -0.0339 0.0138 1.0000
16.750 1.5374 0.06966 0.06368 -0.0344 0.0134 1.0000
17.000 1.5298 0.07394 0.06807 -0.0352 0.0131 1.0000
17.250 1.5203 0.07860 0.07285 -0.0361 0.0128 1.0000
17.500 1.5131 0.08303 0.07738 -0.0371 0.0127 1.0000
17.750 1.5056 0.08756 0.08204 -0.0383 0.0125 1.0000
18.000 1.4969 0.09230 0.08690 -0.0396 0.0123 1.0000
18.250 1.4874 0.09725 0.09197 -0.0411 0.0121 1.0000
18.500 1.4771 0.10239 0.09723 -0.0427 0.0119 1.0000
18.750 1.4663 0.10770 0.10266 -0.0445 0.0118 1.0000
19.000 1.4551 0.11312 0.10819 -0.0465 0.0116 1.0000
19.250 1.4436 0.11865 0.11384 -0.0487 0.0115 1.0000
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