CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 100,000 Max Cl/Cd: 53.21 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkw-il-100000.txt Download as CSV file: xf-clarkw-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK W 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3558 0.10563 0.10036 -0.0358 1.0000 0.1266
-9.000 -0.3949 0.10547 0.10040 -0.0384 1.0000 0.1291
-8.750 -0.4340 0.10512 0.10023 -0.0378 1.0000 0.1295
-8.500 -0.3757 0.09776 0.09273 -0.0347 1.0000 0.1324
-8.250 -0.3690 0.09547 0.09047 -0.0325 1.0000 0.1357
-8.000 -0.3779 0.09372 0.08881 -0.0306 1.0000 0.1392
-7.750 -0.4029 0.09266 0.08787 -0.0282 1.0000 0.1420
-7.500 -0.4414 0.09197 0.08733 -0.0264 1.0000 0.1436
-7.250 -0.4904 0.09033 0.08573 -0.0312 1.0000 0.1450
-7.000 -0.4656 0.08642 0.08190 -0.0238 1.0000 0.1470
-6.750 -0.4592 0.08441 0.07992 -0.0201 1.0000 0.1496
-6.500 -0.4635 0.08233 0.07788 -0.0184 1.0000 0.1529
-6.000 -0.4846 0.07586 0.07139 -0.0220 1.0000 0.1624
-5.750 -0.4794 0.07361 0.06917 -0.0191 1.0000 0.1645
-5.500 -0.4752 0.07134 0.06691 -0.0178 1.0000 0.1683
-5.250 -0.4687 0.04651 0.04045 -0.0373 1.0000 0.1015
-5.000 -0.4515 0.04339 0.03718 -0.0370 1.0000 0.0982
-4.750 -0.4332 0.03969 0.03310 -0.0374 1.0000 0.0969
-4.500 -0.4125 0.03628 0.02923 -0.0377 1.0000 0.0956
-4.250 -0.3754 0.03271 0.02499 -0.0406 0.9964 0.0939
-4.000 -0.3347 0.03029 0.02201 -0.0436 0.9919 0.0943
-3.750 -0.2949 0.02867 0.01993 -0.0462 0.9866 0.0963
-3.500 -0.2522 0.02768 0.01845 -0.0491 0.9814 0.1006
-3.250 -0.2152 0.02646 0.01726 -0.0514 0.9750 0.1055
-3.000 -0.1692 0.02568 0.01629 -0.0548 0.9701 0.1128
-2.750 -0.1353 0.02481 0.01549 -0.0562 0.9619 0.1227
-2.500 -0.0889 0.02405 0.01485 -0.0599 0.9565 0.1513
-2.250 -0.0561 0.02344 0.01446 -0.0611 0.9471 0.1979
-2.000 -0.0087 0.02337 0.01455 -0.0650 0.9411 0.2471
-1.750 0.0203 0.02343 0.01471 -0.0655 0.9302 0.2873
-1.500 0.0575 0.02345 0.01486 -0.0674 0.9219 0.3331
-1.250 0.0946 0.02318 0.01470 -0.0692 0.9132 0.3783
-1.000 0.1286 0.02284 0.01446 -0.0703 0.9042 0.4212
-0.750 0.1690 0.02225 0.01410 -0.0724 0.8967 0.4696
-0.500 0.2012 0.02169 0.01388 -0.0731 0.8873 0.5278
-0.250 0.2722 0.02033 0.01373 -0.0800 0.8835 1.0000
0.000 0.3303 0.02007 0.01321 -0.0853 0.8787 1.0000
0.250 0.3585 0.02009 0.01309 -0.0851 0.8663 1.0000
0.500 0.3968 0.01993 0.01280 -0.0866 0.8571 1.0000
0.750 0.4393 0.01959 0.01236 -0.0886 0.8488 1.0000
1.000 0.4697 0.01946 0.01215 -0.0886 0.8373 1.0000
1.250 0.5164 0.01889 0.01151 -0.0911 0.8307 1.0000
1.500 0.5430 0.01876 0.01133 -0.0902 0.8175 1.0000
1.750 0.5728 0.01854 0.01107 -0.0898 0.8051 1.0000
2.000 0.6099 0.01809 0.01057 -0.0905 0.7950 1.0000
2.250 0.6426 0.01774 0.01018 -0.0904 0.7827 1.0000
2.500 0.6699 0.01755 0.00995 -0.0895 0.7677 1.0000
2.750 0.6977 0.01735 0.00972 -0.0887 0.7524 1.0000
3.000 0.7256 0.01718 0.00950 -0.0879 0.7365 1.0000
3.250 0.7534 0.01703 0.00930 -0.0870 0.7197 1.0000
3.500 0.7809 0.01693 0.00914 -0.0862 0.7024 1.0000
3.750 0.8085 0.01687 0.00901 -0.0854 0.6847 1.0000
4.000 0.8313 0.01701 0.00911 -0.0840 0.6646 1.0000
4.250 0.8554 0.01715 0.00920 -0.0828 0.6451 1.0000
4.500 0.8801 0.01732 0.00931 -0.0818 0.6263 1.0000
4.750 0.9050 0.01755 0.00946 -0.0808 0.6081 1.0000
5.000 0.9296 0.01783 0.00967 -0.0798 0.5906 1.0000
5.250 0.9538 0.01816 0.00994 -0.0789 0.5737 1.0000
5.500 0.9776 0.01853 0.01027 -0.0779 0.5574 1.0000
5.750 1.0011 0.01890 0.01060 -0.0768 0.5407 1.0000
6.000 1.0241 0.01926 0.01087 -0.0756 0.5233 1.0000
6.250 1.0450 0.01964 0.01124 -0.0741 0.5056 1.0000
6.500 1.0672 0.02006 0.01165 -0.0729 0.4895 1.0000
6.750 1.0907 0.02053 0.01208 -0.0720 0.4750 1.0000
7.000 1.1121 0.02102 0.01259 -0.0707 0.4601 1.0000
7.250 1.1329 0.02147 0.01305 -0.0694 0.4442 1.0000
7.500 1.1530 0.02187 0.01341 -0.0678 0.4265 1.0000
7.750 1.1695 0.02225 0.01384 -0.0657 0.4077 1.0000
8.000 1.1860 0.02263 0.01427 -0.0636 0.3891 1.0000
8.250 1.2025 0.02304 0.01472 -0.0616 0.3712 1.0000
8.500 1.2180 0.02346 0.01519 -0.0594 0.3529 1.0000
8.750 1.2319 0.02387 0.01563 -0.0569 0.3337 1.0000
9.000 1.2437 0.02434 0.01610 -0.0542 0.3132 1.0000
9.250 1.2512 0.02485 0.01670 -0.0509 0.2886 1.0000
9.500 1.2555 0.02552 0.01736 -0.0472 0.2605 1.0000
9.750 1.2544 0.02644 0.01820 -0.0427 0.2286 1.0000
10.000 1.2500 0.02781 0.01935 -0.0382 0.1956 1.0000
10.250 1.2457 0.02957 0.02086 -0.0342 0.1668 1.0000
10.500 1.2436 0.03153 0.02261 -0.0308 0.1459 1.0000
10.750 1.2451 0.03348 0.02444 -0.0279 0.1306 1.0000
11.000 1.2500 0.03541 0.02625 -0.0255 0.1192 1.0000
11.250 1.2589 0.03725 0.02796 -0.0236 0.1098 1.0000
11.500 1.2696 0.03900 0.02984 -0.0219 0.1020 1.0000
11.750 1.2885 0.04088 0.03153 -0.0210 0.0950 1.0000
12.000 1.2979 0.04262 0.03351 -0.0192 0.0898 1.0000
12.250 1.3259 0.04465 0.03528 -0.0193 0.0836 1.0000
12.500 1.3322 0.04659 0.03757 -0.0173 0.0806 1.0000
12.750 1.3411 0.04861 0.03978 -0.0157 0.0771 1.0000
13.000 1.3744 0.05115 0.04209 -0.0165 0.0723 1.0000
13.250 1.3715 0.05349 0.04481 -0.0140 0.0710 1.0000
13.500 1.3696 0.05620 0.04786 -0.0118 0.0695 1.0000
13.750 1.3665 0.05907 0.05101 -0.0099 0.0680 1.0000
14.000 1.3641 0.06194 0.05411 -0.0083 0.0664 1.0000
14.250 1.3632 0.06472 0.05704 -0.0071 0.0648 1.0000
14.500 1.3692 0.06763 0.05999 -0.0063 0.0630 1.0000
14.750 1.3671 0.07212 0.06463 -0.0055 0.0620 1.0000
15.000 1.3473 0.07630 0.06912 -0.0044 0.0618 1.0000
15.250 1.3258 0.08098 0.07408 -0.0040 0.0618 1.0000
15.500 1.3028 0.08617 0.07955 -0.0044 0.0618 1.0000
15.750 1.2785 0.09192 0.08554 -0.0055 0.0618 1.0000
16.000 1.2534 0.09824 0.09209 -0.0074 0.0620 1.0000
16.250 1.2201 0.10550 0.09964 -0.0110 0.0624 1.0000
16.500 1.0532 0.14296 0.13773 -0.0374 0.0717 1.0000
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