CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 100,000 Max Cl/Cd: 55.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkz-il-100000-n5.txt Download as CSV file: xf-clarkz-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3248 0.09932 0.09420 -0.0386 1.0000 0.0788
-8.500 -0.3521 0.09789 0.09293 -0.0387 1.0000 0.0805
-8.250 -0.3783 0.09668 0.09184 -0.0367 1.0000 0.0808
-8.000 -0.3858 0.09229 0.08748 -0.0443 0.9936 0.0812
-7.750 -0.3709 0.08579 0.08087 -0.0550 0.9844 0.0814
-7.250 -0.3460 0.06588 0.06065 -0.0667 0.9717 0.0518
-7.000 -0.3286 0.06217 0.05687 -0.0695 0.9636 0.0513
-6.750 -0.3051 0.05725 0.05177 -0.0746 0.9584 0.0508
-6.500 -0.2896 0.05209 0.04635 -0.0781 0.9486 0.0507
-6.250 -0.2659 0.04588 0.03965 -0.0831 0.9430 0.0512
-6.000 -0.2482 0.04185 0.03523 -0.0843 0.9337 0.0511
-5.750 -0.2202 0.03801 0.03096 -0.0868 0.9290 0.0510
-5.500 -0.1996 0.03515 0.02770 -0.0870 0.9202 0.0510
-5.250 -0.1710 0.03234 0.02442 -0.0883 0.9147 0.0511
-5.000 -0.1434 0.03007 0.02169 -0.0890 0.9085 0.0514
-4.750 -0.1169 0.02830 0.01956 -0.0891 0.9010 0.0522
-4.500 -0.0841 0.02707 0.01824 -0.0905 0.8965 0.0536
-4.250 -0.0589 0.02611 0.01715 -0.0901 0.8880 0.0549
-4.000 -0.0276 0.02486 0.01568 -0.0908 0.8822 0.0560
-3.750 0.0017 0.02373 0.01433 -0.0909 0.8754 0.0569
-3.500 0.0303 0.02274 0.01316 -0.0909 0.8677 0.0580
-3.250 0.0639 0.02174 0.01198 -0.0916 0.8628 0.0593
-3.000 0.0885 0.02106 0.01122 -0.0908 0.8527 0.0607
-2.750 0.1203 0.02034 0.01054 -0.0914 0.8468 0.0635
-2.500 0.1451 0.01988 0.01006 -0.0906 0.8367 0.0667
-2.250 0.1765 0.01923 0.00931 -0.0909 0.8303 0.0699
-2.000 0.2007 0.01876 0.00890 -0.0900 0.8198 0.0731
-1.750 0.2307 0.01824 0.00834 -0.0901 0.8127 0.0785
-1.500 0.2558 0.01787 0.00802 -0.0893 0.8022 0.0868
-1.250 0.2838 0.01745 0.00764 -0.0891 0.7936 0.1027
-1.000 0.3106 0.01702 0.00731 -0.0886 0.7839 0.1312
-0.750 0.3370 0.01661 0.00709 -0.0882 0.7739 0.1832
-0.500 0.3643 0.01583 0.00686 -0.0881 0.7651 0.3297
-0.250 0.4033 0.01417 0.00702 -0.0887 0.7554 0.9365
0.250 0.4775 0.01414 0.00659 -0.0920 0.7343 1.0000
0.500 0.5021 0.01421 0.00651 -0.0911 0.7231 1.0000
0.750 0.5284 0.01425 0.00638 -0.0905 0.7128 1.0000
1.000 0.5527 0.01435 0.00636 -0.0896 0.7007 1.0000
1.250 0.5774 0.01446 0.00636 -0.0888 0.6889 1.0000
1.500 0.6030 0.01455 0.00632 -0.0881 0.6776 1.0000
1.750 0.6284 0.01466 0.00631 -0.0874 0.6658 1.0000
2.000 0.6528 0.01481 0.00638 -0.0866 0.6530 1.0000
2.250 0.6777 0.01495 0.00643 -0.0859 0.6405 1.0000
2.500 0.7031 0.01509 0.00647 -0.0852 0.6284 1.0000
2.750 0.7283 0.01524 0.00654 -0.0845 0.6158 1.0000
3.000 0.7526 0.01543 0.00667 -0.0837 0.6022 1.0000
3.250 0.7771 0.01563 0.00680 -0.0829 0.5890 1.0000
3.500 0.8018 0.01583 0.00694 -0.0822 0.5758 1.0000
3.750 0.8265 0.01605 0.00707 -0.0814 0.5630 1.0000
4.000 0.8510 0.01628 0.00724 -0.0807 0.5499 1.0000
4.250 0.8749 0.01653 0.00747 -0.0799 0.5361 1.0000
4.500 0.8989 0.01680 0.00770 -0.0791 0.5229 1.0000
4.750 0.9228 0.01708 0.00793 -0.0783 0.5099 1.0000
5.000 0.9467 0.01738 0.00818 -0.0775 0.4973 1.0000
5.250 0.9703 0.01770 0.00845 -0.0767 0.4846 1.0000
5.500 0.9932 0.01803 0.00877 -0.0758 0.4709 1.0000
5.750 1.0156 0.01837 0.00909 -0.0748 0.4565 1.0000
6.000 1.0373 0.01873 0.00940 -0.0737 0.4409 1.0000
6.250 1.0579 0.01911 0.00972 -0.0724 0.4237 1.0000
6.500 1.0780 0.01951 0.01007 -0.0711 0.4062 1.0000
6.750 1.0982 0.01993 0.01046 -0.0698 0.3905 1.0000
7.000 1.1188 0.02037 0.01090 -0.0687 0.3770 1.0000
7.250 1.1391 0.02082 0.01135 -0.0675 0.3642 1.0000
7.500 1.1587 0.02130 0.01183 -0.0662 0.3513 1.0000
7.750 1.1776 0.02180 0.01233 -0.0649 0.3379 1.0000
8.000 1.1958 0.02231 0.01288 -0.0634 0.3237 1.0000
8.250 1.2132 0.02286 0.01347 -0.0619 0.3094 1.0000
8.500 1.2296 0.02344 0.01408 -0.0603 0.2947 1.0000
8.750 1.2448 0.02408 0.01473 -0.0585 0.2794 1.0000
9.000 1.2578 0.02476 0.01542 -0.0564 0.2633 1.0000
9.250 1.2687 0.02552 0.01618 -0.0541 0.2464 1.0000
9.500 1.2782 0.02641 0.01705 -0.0517 0.2291 1.0000
9.750 1.2865 0.02742 0.01802 -0.0493 0.2121 1.0000
10.000 1.2943 0.02853 0.01911 -0.0470 0.1962 1.0000
10.250 1.3008 0.02979 0.02033 -0.0448 0.1824 1.0000
10.500 1.3073 0.03112 0.02166 -0.0427 0.1704 1.0000
10.750 1.3139 0.03252 0.02309 -0.0407 0.1604 1.0000
11.000 1.3185 0.03409 0.02464 -0.0388 0.1528 1.0000
11.250 1.3254 0.03558 0.02620 -0.0371 0.1457 1.0000
11.500 1.3291 0.03733 0.02794 -0.0354 0.1405 1.0000
11.750 1.3369 0.03887 0.02958 -0.0340 0.1355 1.0000
12.000 1.3433 0.04054 0.03134 -0.0326 0.1314 1.0000
12.250 1.3484 0.04234 0.03317 -0.0313 0.1280 1.0000
12.500 1.3550 0.04408 0.03495 -0.0301 0.1250 1.0000
12.750 1.3630 0.04576 0.03677 -0.0290 0.1217 1.0000
13.000 1.3695 0.04757 0.03868 -0.0280 0.1184 1.0000
13.250 1.3746 0.04951 0.04068 -0.0271 0.1153 1.0000
13.500 1.3802 0.05143 0.04260 -0.0261 0.1124 1.0000
13.750 1.3850 0.05352 0.04490 -0.0254 0.1092 1.0000
14.000 1.3883 0.05577 0.04728 -0.0248 0.1059 1.0000
14.250 1.3900 0.05814 0.04973 -0.0244 0.1028 1.0000
14.500 1.3927 0.06044 0.05201 -0.0238 0.0998 1.0000
14.750 1.3921 0.06330 0.05514 -0.0237 0.0969 1.0000
15.000 1.3913 0.06623 0.05823 -0.0237 0.0938 1.0000
15.250 1.3901 0.06921 0.06131 -0.0238 0.0911 1.0000
15.500 1.3903 0.07200 0.06410 -0.0239 0.0884 1.0000
15.750 1.3857 0.07572 0.06806 -0.0245 0.0857 1.0000
16.000 1.3804 0.07963 0.07218 -0.0254 0.0829 1.0000
16.250 1.3754 0.08354 0.07622 -0.0264 0.0803 1.0000
16.500 1.3713 0.08732 0.08008 -0.0274 0.0779 1.0000
16.750 1.3668 0.09129 0.08418 -0.0285 0.0757 1.0000
17.000 1.3575 0.09631 0.08947 -0.0303 0.0734 1.0000
17.250 1.3483 0.10135 0.09470 -0.0323 0.0709 1.0000
17.500 1.3402 0.10628 0.09976 -0.0343 0.0686 1.0000
17.750 1.3346 0.11071 0.10422 -0.0362 0.0664 1.0000
18.000 1.3197 0.11727 0.11106 -0.0394 0.0642 1.0000
18.250 1.3049 0.12397 0.11798 -0.0427 0.0619 1.0000
18.500 1.2923 0.13031 0.12447 -0.0461 0.0596 1.0000
18.750 1.2855 0.13547 0.12967 -0.0490 0.0573 1.0000
19.000 1.2638 0.14420 0.13863 -0.0540 0.0553 1.0000
19.250 1.2372 0.15444 0.14910 -0.0602 0.0534 1.0000
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