CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.63 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkz-il-1000000.txt Download as CSV file: xf-clarkz-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3198 0.08356 0.08187 -0.0505 0.9950 0.0269
-8.750 -0.2348 0.05872 0.05707 -0.0692 0.9703 0.0292
-8.500 -0.4010 0.03362 0.03097 -0.0990 0.9520 0.0290
-8.250 -0.3843 0.03192 0.02920 -0.0987 0.9431 0.0293
-8.000 -0.3775 0.02693 0.02383 -0.0983 0.9323 0.0275
-7.750 -0.3690 0.02210 0.01839 -0.0975 0.9225 0.0274
-7.500 -0.3509 0.01967 0.01561 -0.0967 0.9134 0.0274
-7.250 -0.3293 0.01803 0.01369 -0.0961 0.9054 0.0276
-7.000 -0.3061 0.01679 0.01222 -0.0955 0.8969 0.0278
-6.750 -0.2815 0.01583 0.01108 -0.0950 0.8889 0.0280
-6.500 -0.2563 0.01508 0.01016 -0.0945 0.8802 0.0282
-6.250 -0.2303 0.01451 0.00945 -0.0941 0.8719 0.0284
-6.000 -0.2047 0.01379 0.00856 -0.0937 0.8628 0.0288
-5.750 -0.1800 0.01261 0.00726 -0.0933 0.8538 0.0293
-5.500 -0.1540 0.01203 0.00659 -0.0929 0.8444 0.0295
-5.250 -0.1274 0.01157 0.00609 -0.0926 0.8351 0.0299
-5.000 -0.1008 0.01118 0.00563 -0.0923 0.8259 0.0302
-4.750 -0.0738 0.01082 0.00522 -0.0920 0.8163 0.0305
-4.500 -0.0469 0.01049 0.00482 -0.0917 0.8071 0.0309
-4.250 -0.0200 0.01018 0.00446 -0.0914 0.7972 0.0313
-4.000 0.0071 0.00989 0.00411 -0.0911 0.7876 0.0317
-3.500 0.0613 0.00941 0.00352 -0.0906 0.7679 0.0326
-3.250 0.0886 0.00923 0.00328 -0.0903 0.7584 0.0331
-3.000 0.1158 0.00900 0.00301 -0.0901 0.7485 0.0337
-2.750 0.1425 0.00867 0.00264 -0.0898 0.7394 0.0346
-2.500 0.1698 0.00851 0.00244 -0.0895 0.7297 0.0354
-2.250 0.1974 0.00837 0.00228 -0.0894 0.7202 0.0363
-2.000 0.2248 0.00828 0.00213 -0.0891 0.7108 0.0373
-1.750 0.2527 0.00817 0.00200 -0.0890 0.7012 0.0383
-1.500 0.2801 0.00806 0.00184 -0.0888 0.6917 0.0397
-1.250 0.3076 0.00795 0.00172 -0.0886 0.6817 0.0421
-1.000 0.3354 0.00788 0.00163 -0.0884 0.6721 0.0447
-0.750 0.3626 0.00780 0.00154 -0.0882 0.6617 0.0516
-0.500 0.3898 0.00760 0.00148 -0.0880 0.6516 0.0894
-0.250 0.4170 0.00749 0.00146 -0.0878 0.6416 0.1282
0.000 0.4441 0.00741 0.00144 -0.0876 0.6305 0.1648
0.500 0.4968 0.00691 0.00146 -0.0872 0.6090 0.3697
0.750 0.5204 0.00637 0.00150 -0.0866 0.5974 0.5984
1.000 0.5413 0.00584 0.00159 -0.0851 0.5857 0.8121
1.250 0.5649 0.00566 0.00171 -0.0835 0.5740 0.9474
1.500 0.6112 0.00579 0.00177 -0.0874 0.5597 0.9876
1.750 0.6600 0.00593 0.00182 -0.0920 0.5437 0.9985
2.000 0.6901 0.00606 0.00186 -0.0925 0.5291 1.0000
2.250 0.7143 0.00619 0.00191 -0.0917 0.5139 1.0000
2.500 0.7384 0.00635 0.00198 -0.0909 0.4960 1.0000
2.750 0.7623 0.00652 0.00205 -0.0900 0.4765 1.0000
3.000 0.7863 0.00669 0.00213 -0.0892 0.4602 1.0000
3.250 0.8104 0.00686 0.00223 -0.0884 0.4448 1.0000
3.500 0.8345 0.00704 0.00233 -0.0876 0.4288 1.0000
3.750 0.8587 0.00723 0.00243 -0.0869 0.4131 1.0000
4.000 0.8832 0.00742 0.00255 -0.0862 0.3992 1.0000
4.500 0.9328 0.00781 0.00280 -0.0850 0.3713 1.0000
4.750 0.9581 0.00799 0.00294 -0.0845 0.3594 1.0000
5.000 0.9833 0.00818 0.00308 -0.0840 0.3486 1.0000
5.500 1.0338 0.00857 0.00338 -0.0830 0.3269 1.0000
5.750 1.0588 0.00878 0.00355 -0.0825 0.3155 1.0000
6.000 1.0836 0.00902 0.00373 -0.0820 0.3036 1.0000
6.250 1.1085 0.00924 0.00391 -0.0815 0.2920 1.0000
6.500 1.1334 0.00947 0.00410 -0.0810 0.2803 1.0000
6.750 1.1578 0.00973 0.00431 -0.0805 0.2675 1.0000
7.000 1.1818 0.01002 0.00454 -0.0799 0.2531 1.0000
7.250 1.2051 0.01035 0.00480 -0.0792 0.2360 1.0000
7.500 1.2270 0.01078 0.00510 -0.0783 0.2149 1.0000
7.750 1.2480 0.01127 0.00546 -0.0773 0.1903 1.0000
8.000 1.2672 0.01188 0.00590 -0.0760 0.1621 1.0000
8.250 1.2856 0.01252 0.00639 -0.0745 0.1361 1.0000
8.500 1.3041 0.01314 0.00687 -0.0732 0.1163 1.0000
8.750 1.3239 0.01364 0.00730 -0.0720 0.1047 1.0000
9.000 1.3446 0.01407 0.00771 -0.0709 0.0977 1.0000
9.250 1.3640 0.01455 0.00815 -0.0697 0.0912 1.0000
9.500 1.3842 0.01491 0.00853 -0.0685 0.0880 1.0000
9.750 1.4030 0.01531 0.00893 -0.0671 0.0849 1.0000
10.000 1.4204 0.01578 0.00940 -0.0656 0.0815 1.0000
10.250 1.4374 0.01627 0.00991 -0.0640 0.0784 1.0000
10.500 1.4569 0.01663 0.01030 -0.0628 0.0769 1.0000
10.750 1.4751 0.01707 0.01076 -0.0615 0.0746 1.0000
11.000 1.4917 0.01759 0.01130 -0.0600 0.0722 1.0000
11.250 1.5070 0.01821 0.01193 -0.0584 0.0696 1.0000
11.500 1.5235 0.01876 0.01251 -0.0570 0.0678 1.0000
11.750 1.5413 0.01923 0.01304 -0.0559 0.0664 1.0000
12.000 1.5577 0.01980 0.01364 -0.0546 0.0644 1.0000
12.250 1.5720 0.02051 0.01434 -0.0531 0.0615 1.0000
12.500 1.5860 0.02127 0.01513 -0.0516 0.0587 1.0000
12.750 1.6019 0.02191 0.01581 -0.0505 0.0564 1.0000
13.000 1.6144 0.02280 0.01668 -0.0490 0.0527 1.0000
13.250 1.6270 0.02370 0.01761 -0.0477 0.0489 1.0000
13.500 1.6359 0.02489 0.01877 -0.0461 0.0428 1.0000
13.750 1.6379 0.02666 0.02046 -0.0440 0.0317 1.0000
14.000 1.6334 0.02901 0.02276 -0.0417 0.0222 1.0000
14.250 1.6345 0.03104 0.02483 -0.0400 0.0192 1.0000
14.500 1.6374 0.03299 0.02683 -0.0386 0.0179 1.0000
14.750 1.6381 0.03521 0.02910 -0.0373 0.0167 1.0000
15.000 1.6422 0.03719 0.03117 -0.0363 0.0161 1.0000
15.250 1.6448 0.03936 0.03342 -0.0354 0.0156 1.0000
15.500 1.6455 0.04180 0.03594 -0.0346 0.0150 1.0000
15.750 1.6444 0.04452 0.03874 -0.0340 0.0146 1.0000
16.000 1.6409 0.04761 0.04191 -0.0335 0.0141 1.0000
16.250 1.6353 0.05104 0.04544 -0.0332 0.0138 1.0000
16.500 1.6351 0.05395 0.04845 -0.0331 0.0136 1.0000
16.750 1.6332 0.05714 0.05173 -0.0331 0.0133 1.0000
17.000 1.6296 0.06060 0.05529 -0.0333 0.0131 1.0000
17.250 1.6244 0.06434 0.05913 -0.0336 0.0129 1.0000
17.500 1.6180 0.06835 0.06324 -0.0342 0.0127 1.0000
17.750 1.6104 0.07260 0.06759 -0.0349 0.0125 1.0000
18.000 1.6014 0.07709 0.07219 -0.0358 0.0123 1.0000
18.250 1.5906 0.08195 0.07716 -0.0369 0.0122 1.0000
18.500 1.5785 0.08710 0.08242 -0.0382 0.0120 1.0000
18.750 1.5651 0.09250 0.08793 -0.0397 0.0119 1.0000
19.000 1.5496 0.09830 0.09384 -0.0414 0.0118 1.0000
19.250 1.5335 0.10431 0.09996 -0.0434 0.0117 1.0000
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