CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 500,000 Max Cl/Cd: 92.78 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkx-il-500000-n5.txt Download as CSV file: xf-clarkx-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK X 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
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0427 0.03696 0.03359 -0.0878 1.0000 0.0159
-14.250 -1.0539 0.03397 0.03044 -0.0876 1.0000 0.0162
-14.000 -1.0577 0.03208 0.02841 -0.0857 1.0000 0.0167
-13.750 -1.0560 0.03049 0.02667 -0.0837 1.0000 0.0173
-13.500 -1.0528 0.02910 0.02513 -0.0814 1.0000 0.0178
-13.250 -1.0470 0.02797 0.02391 -0.0791 1.0000 0.0184
-13.000 -1.0380 0.02715 0.02304 -0.0769 1.0000 0.0190
-12.750 -1.0201 0.02635 0.02215 -0.0762 0.9990 0.0198
-12.500 -0.9929 0.02539 0.02107 -0.0774 0.9967 0.0208
-12.250 -0.9654 0.02437 0.01988 -0.0787 0.9945 0.0217
-12.000 -0.9385 0.02343 0.01876 -0.0796 0.9918 0.0224
-11.750 -0.9112 0.02262 0.01790 -0.0805 0.9889 0.0233
-11.500 -0.8811 0.02209 0.01730 -0.0817 0.9866 0.0242
-11.250 -0.8502 0.02152 0.01665 -0.0831 0.9848 0.0251
-11.000 -0.8219 0.02088 0.01590 -0.0839 0.9819 0.0261
-10.750 -0.7939 0.02023 0.01511 -0.0845 0.9784 0.0269
-10.500 -0.7642 0.01964 0.01438 -0.0854 0.9755 0.0275
-10.250 -0.7352 0.01880 0.01347 -0.0865 0.9730 0.0285
-10.000 -0.7091 0.01835 0.01297 -0.0865 0.9677 0.0293
-9.750 -0.6803 0.01793 0.01249 -0.0871 0.9637 0.0302
-9.500 -0.6502 0.01748 0.01197 -0.0879 0.9606 0.0311
-9.250 -0.6245 0.01704 0.01144 -0.0878 0.9547 0.0320
-9.000 -0.5968 0.01657 0.01086 -0.0880 0.9497 0.0328
-8.750 -0.5682 0.01615 0.01032 -0.0884 0.9454 0.0335
-8.500 -0.5440 0.01550 0.00960 -0.0879 0.9385 0.0342
-8.250 -0.5176 0.01491 0.00894 -0.0879 0.9327 0.0351
-8.000 -0.4915 0.01451 0.00850 -0.0877 0.9264 0.0359
-7.750 -0.4651 0.01416 0.00808 -0.0875 0.9195 0.0368
-7.500 -0.4384 0.01377 0.00763 -0.0873 0.9134 0.0375
-7.250 -0.4125 0.01340 0.00718 -0.0870 0.9057 0.0383
-7.000 -0.3858 0.01304 0.00674 -0.0868 0.8991 0.0392
-6.750 -0.3596 0.01271 0.00633 -0.0865 0.8911 0.0399
-6.500 -0.3328 0.01241 0.00594 -0.0863 0.8840 0.0406
-6.250 -0.3067 0.01205 0.00552 -0.0860 0.8757 0.0416
-6.000 -0.2802 0.01171 0.00513 -0.0857 0.8682 0.0432
-5.750 -0.2535 0.01145 0.00484 -0.0855 0.8598 0.0446
-5.500 -0.2265 0.01122 0.00455 -0.0853 0.8521 0.0460
-5.250 -0.1995 0.01100 0.00428 -0.0851 0.8437 0.0475
-5.000 -0.1723 0.01081 0.00401 -0.0849 0.8359 0.0489
-4.750 -0.1452 0.01061 0.00376 -0.0847 0.8274 0.0504
-4.500 -0.1182 0.01037 0.00349 -0.0845 0.8194 0.0531
-4.250 -0.0910 0.01020 0.00329 -0.0843 0.8110 0.0557
-4.000 -0.0636 0.01006 0.00311 -0.0842 0.8029 0.0584
-3.750 -0.0362 0.00995 0.00293 -0.0840 0.7945 0.0610
-3.500 -0.0089 0.00977 0.00275 -0.0839 0.7863 0.0656
-3.250 0.0184 0.00965 0.00260 -0.0837 0.7780 0.0697
-3.000 0.0460 0.00955 0.00246 -0.0836 0.7696 0.0733
-2.500 0.1008 0.00932 0.00220 -0.0833 0.7527 0.0861
-2.250 0.1280 0.00920 0.00209 -0.0832 0.7443 0.0973
-2.000 0.1554 0.00908 0.00200 -0.0830 0.7350 0.1128
-1.750 0.1825 0.00896 0.00192 -0.0829 0.7257 0.1326
-1.500 0.2095 0.00885 0.00184 -0.0827 0.7153 0.1540
-1.250 0.2365 0.00872 0.00177 -0.0825 0.7046 0.1801
-1.000 0.2630 0.00854 0.00174 -0.0823 0.6947 0.2358
-0.750 0.2900 0.00844 0.00172 -0.0821 0.6848 0.2752
-0.500 0.3173 0.00839 0.00170 -0.0820 0.6750 0.3007
-0.250 0.3444 0.00833 0.00168 -0.0818 0.6654 0.3266
0.000 0.3713 0.00824 0.00167 -0.0816 0.6549 0.3611
0.250 0.3978 0.00810 0.00168 -0.0814 0.6448 0.4152
0.500 0.4230 0.00783 0.00171 -0.0810 0.6342 0.5224
0.750 0.4464 0.00746 0.00176 -0.0801 0.6231 0.6623
1.000 0.4673 0.00709 0.00186 -0.0784 0.6118 0.8101
1.250 0.4916 0.00701 0.00196 -0.0772 0.6001 0.8995
1.500 0.5240 0.00710 0.00203 -0.0779 0.5833 0.9419
1.750 0.5608 0.00727 0.00209 -0.0798 0.5610 0.9712
2.000 0.5969 0.00743 0.00215 -0.0817 0.5414 0.9861
2.250 0.6333 0.00757 0.00222 -0.0836 0.5266 0.9957
2.500 0.6648 0.00772 0.00229 -0.0845 0.5108 1.0000
2.750 0.6885 0.00788 0.00237 -0.0836 0.4950 1.0000
3.000 0.7122 0.00805 0.00247 -0.0828 0.4795 1.0000
3.250 0.7360 0.00822 0.00258 -0.0820 0.4648 1.0000
3.500 0.7599 0.00840 0.00269 -0.0812 0.4498 1.0000
3.750 0.7839 0.00859 0.00283 -0.0804 0.4343 1.0000
4.000 0.8079 0.00880 0.00297 -0.0797 0.4185 1.0000
4.250 0.8318 0.00902 0.00312 -0.0790 0.4015 1.0000
4.500 0.8557 0.00926 0.00330 -0.0782 0.3840 1.0000
4.750 0.8796 0.00951 0.00348 -0.0775 0.3678 1.0000
5.000 0.9037 0.00975 0.00368 -0.0769 0.3533 1.0000
5.250 0.9278 0.01000 0.00389 -0.0762 0.3394 1.0000
5.500 0.9518 0.01027 0.00411 -0.0755 0.3260 1.0000
5.750 0.9752 0.01057 0.00435 -0.0748 0.3084 1.0000
6.000 0.9979 0.01092 0.00461 -0.0740 0.2875 1.0000
6.250 1.0199 0.01133 0.00491 -0.0730 0.2642 1.0000
6.500 1.0413 0.01179 0.00524 -0.0720 0.2383 1.0000
6.750 1.0629 0.01223 0.00557 -0.0711 0.2156 1.0000
7.000 1.0847 0.01264 0.00591 -0.0702 0.1978 1.0000
7.250 1.1059 0.01310 0.00628 -0.0692 0.1800 1.0000
7.500 1.1268 0.01357 0.00667 -0.0681 0.1628 1.0000
7.750 1.1477 0.01403 0.00707 -0.0671 0.1466 1.0000
8.000 1.1665 0.01463 0.00754 -0.0658 0.1218 1.0000
8.250 1.1798 0.01560 0.00825 -0.0637 0.0815 1.0000
8.500 1.1929 0.01655 0.00903 -0.0616 0.0514 1.0000
8.750 1.2061 0.01736 0.00974 -0.0594 0.0357 1.0000
9.000 1.2216 0.01799 0.01036 -0.0575 0.0294 1.0000
9.250 1.2377 0.01860 0.01099 -0.0558 0.0254 1.0000
9.500 1.2533 0.01925 0.01166 -0.0541 0.0223 1.0000
9.750 1.2692 0.01988 0.01234 -0.0525 0.0204 1.0000
10.000 1.2847 0.02055 0.01304 -0.0509 0.0187 1.0000
10.250 1.2986 0.02132 0.01384 -0.0492 0.0172 1.0000
10.500 1.3125 0.02211 0.01468 -0.0475 0.0162 1.0000
10.750 1.3266 0.02289 0.01553 -0.0460 0.0152 1.0000
11.000 1.3397 0.02376 0.01646 -0.0444 0.0144 1.0000
11.250 1.3514 0.02475 0.01749 -0.0427 0.0137 1.0000
11.500 1.3610 0.02593 0.01872 -0.0410 0.0130 1.0000
11.750 1.3706 0.02713 0.02000 -0.0393 0.0126 1.0000
12.000 1.3810 0.02831 0.02127 -0.0379 0.0122 1.0000
12.250 1.3902 0.02961 0.02265 -0.0365 0.0118 1.0000
12.500 1.3988 0.03101 0.02414 -0.0352 0.0113 1.0000
12.750 1.4066 0.03251 0.02572 -0.0339 0.0109 1.0000
13.000 1.4136 0.03414 0.02741 -0.0328 0.0105 1.0000
13.250 1.4186 0.03599 0.02934 -0.0316 0.0102 1.0000
13.500 1.4207 0.03819 0.03162 -0.0306 0.0099 1.0000
13.750 1.4206 0.04068 0.03420 -0.0296 0.0096 1.0000
14.000 1.4239 0.04290 0.03653 -0.0289 0.0095 1.0000
14.250 1.4256 0.04537 0.03911 -0.0283 0.0093 1.0000
14.500 1.4262 0.04803 0.04188 -0.0278 0.0091 1.0000
14.750 1.4258 0.05091 0.04487 -0.0276 0.0089 1.0000
15.000 1.4242 0.05402 0.04810 -0.0275 0.0088 1.0000
15.250 1.4221 0.05732 0.05150 -0.0276 0.0086 1.0000
15.500 1.4188 0.06084 0.05514 -0.0279 0.0085 1.0000
15.750 1.4148 0.06459 0.05899 -0.0284 0.0084 1.0000
16.000 1.4101 0.06852 0.06303 -0.0291 0.0082 1.0000
16.250 1.4045 0.07268 0.06730 -0.0299 0.0081 1.0000
16.500 1.3982 0.07702 0.07175 -0.0309 0.0080 1.0000
16.750 1.3909 0.08161 0.07645 -0.0322 0.0079 1.0000
17.000 1.3834 0.08632 0.08127 -0.0335 0.0078 1.0000
17.250 1.3750 0.09123 0.08629 -0.0350 0.0077 1.0000
17.500 1.3659 0.09633 0.09149 -0.0367 0.0077 1.0000
17.750 1.3565 0.10154 0.09682 -0.0385 0.0076 1.0000
18.000 1.3468 0.10688 0.10226 -0.0405 0.0075 1.0000
18.250 1.3368 0.11231 0.10778 -0.0425 0.0074 1.0000
18.500 1.3268 0.11777 0.11334 -0.0447 0.0073 1.0000
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Polar data table (+)
Polar graphs
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