CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 50,000 Max Cl/Cd: 36.35 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkk-il-50000-n5.txt Download as CSV file: xf-clarkk-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3918 0.11491 0.10738 -0.0335 1.0000 0.1838
-9.500 -0.4024 0.11242 0.10499 -0.0352 1.0000 0.1843
-9.250 -0.4210 0.09819 0.09074 -0.0441 1.0000 0.1096
-9.000 -0.4071 0.09530 0.08783 -0.0422 1.0000 0.1075
-8.750 -0.4107 0.09206 0.08466 -0.0421 1.0000 0.1061
-8.500 -0.4207 0.08890 0.08160 -0.0419 1.0000 0.1051
-8.250 -0.4360 0.08579 0.07861 -0.0414 1.0000 0.1041
-8.000 -0.4514 0.08209 0.07501 -0.0419 1.0000 0.1029
-7.500 -0.5154 0.06827 0.06095 -0.0477 1.0000 0.0964
-7.250 -0.5171 0.06500 0.05761 -0.0466 1.0000 0.0959
-7.000 -0.5174 0.06167 0.05416 -0.0457 1.0000 0.0954
-6.750 -0.5163 0.05819 0.05049 -0.0451 1.0000 0.0950
-6.500 -0.5140 0.05442 0.04639 -0.0449 1.0000 0.0952
-6.250 -0.5085 0.05075 0.04225 -0.0448 1.0000 0.0959
-6.000 -0.4981 0.04772 0.03881 -0.0444 1.0000 0.0963
-5.750 -0.4804 0.04495 0.03566 -0.0448 0.9986 0.0962
-5.500 -0.4486 0.04207 0.03230 -0.0475 0.9932 0.0962
-5.250 -0.4165 0.03963 0.02938 -0.0499 0.9874 0.0964
-5.000 -0.3841 0.03765 0.02719 -0.0521 0.9819 0.0980
-4.750 -0.3509 0.03609 0.02542 -0.0542 0.9759 0.0999
-4.500 -0.3177 0.03459 0.02360 -0.0560 0.9698 0.1009
-4.250 -0.2823 0.03322 0.02191 -0.0580 0.9639 0.1013
-4.000 -0.2495 0.03210 0.02053 -0.0594 0.9572 0.1018
-3.750 -0.2132 0.03112 0.01932 -0.0613 0.9514 0.1026
-3.500 -0.1816 0.03032 0.01836 -0.0623 0.9439 0.1035
-3.250 -0.1448 0.02963 0.01751 -0.0642 0.9381 0.1059
-3.000 -0.1145 0.02910 0.01681 -0.0648 0.9300 0.1085
-2.750 -0.0773 0.02853 0.01616 -0.0667 0.9241 0.1108
-2.500 -0.0479 0.02809 0.01567 -0.0672 0.9156 0.1125
-2.250 -0.0110 0.02767 0.01519 -0.0690 0.9093 0.1146
-2.000 0.0181 0.02739 0.01484 -0.0695 0.9006 0.1170
-1.750 0.0546 0.02708 0.01446 -0.0712 0.8939 0.1205
-1.500 0.0841 0.02687 0.01424 -0.0716 0.8850 0.1245
-1.250 0.1196 0.02656 0.01400 -0.0732 0.8779 0.1328
-0.750 0.1833 0.02592 0.01381 -0.0751 0.8616 0.2156
-0.500 0.2123 0.02531 0.01382 -0.0757 0.8533 0.3417
-0.250 0.2391 0.02454 0.01386 -0.0754 0.8451 0.5193
0.000 0.2658 0.02384 0.01402 -0.0737 0.8375 0.7735
0.250 0.3171 0.02371 0.01392 -0.0777 0.8290 1.0000
0.500 0.3465 0.02384 0.01387 -0.0779 0.8197 1.0000
0.750 0.3771 0.02392 0.01381 -0.0782 0.8105 1.0000
1.000 0.4023 0.02413 0.01389 -0.0776 0.7994 1.0000
1.250 0.4375 0.02407 0.01370 -0.0785 0.7919 1.0000
1.500 0.4601 0.02432 0.01387 -0.0775 0.7795 1.0000
1.750 0.4877 0.02444 0.01390 -0.0772 0.7689 1.0000
2.000 0.5200 0.02438 0.01376 -0.0774 0.7597 1.0000
2.250 0.5435 0.02459 0.01392 -0.0765 0.7469 1.0000
2.500 0.5703 0.02468 0.01395 -0.0759 0.7352 1.0000
2.750 0.6042 0.02447 0.01370 -0.0761 0.7257 1.0000
3.000 0.6275 0.02463 0.01383 -0.0750 0.7115 1.0000
3.250 0.6522 0.02473 0.01392 -0.0740 0.6975 1.0000
3.500 0.6779 0.02478 0.01396 -0.0731 0.6836 1.0000
3.750 0.7046 0.02478 0.01395 -0.0723 0.6698 1.0000
4.000 0.7319 0.02476 0.01393 -0.0716 0.6560 1.0000
4.250 0.7596 0.02473 0.01389 -0.0709 0.6421 1.0000
4.500 0.7843 0.02485 0.01402 -0.0699 0.6269 1.0000
4.750 0.8082 0.02501 0.01422 -0.0688 0.6111 1.0000
5.000 0.8323 0.02518 0.01441 -0.0677 0.5949 1.0000
5.250 0.8565 0.02536 0.01461 -0.0666 0.5785 1.0000
5.500 0.8807 0.02555 0.01484 -0.0656 0.5617 1.0000
5.750 0.9048 0.02577 0.01507 -0.0645 0.5445 1.0000
6.000 0.9277 0.02608 0.01540 -0.0633 0.5267 1.0000
6.250 0.9495 0.02648 0.01585 -0.0621 0.5084 1.0000
6.500 0.9710 0.02691 0.01631 -0.0608 0.4899 1.0000
6.750 0.9925 0.02739 0.01682 -0.0596 0.4719 1.0000
7.000 1.0138 0.02791 0.01740 -0.0584 0.4543 1.0000
7.250 1.0349 0.02847 0.01800 -0.0571 0.4371 1.0000
7.500 1.0558 0.02909 0.01867 -0.0560 0.4208 1.0000
7.750 1.0765 0.02976 0.01941 -0.0548 0.4053 1.0000
8.000 1.0971 0.03046 0.02017 -0.0536 0.3906 1.0000
8.250 1.1183 0.03119 0.02095 -0.0526 0.3770 1.0000
8.500 1.1396 0.03192 0.02176 -0.0515 0.3639 1.0000
8.750 1.1570 0.03285 0.02283 -0.0501 0.3506 1.0000
9.000 1.1737 0.03376 0.02387 -0.0486 0.3371 1.0000
9.250 1.1864 0.03458 0.02476 -0.0464 0.3212 1.0000
9.500 1.1939 0.03538 0.02557 -0.0437 0.3030 1.0000
9.750 1.1957 0.03623 0.02638 -0.0403 0.2837 1.0000
10.000 1.1927 0.03741 0.02757 -0.0367 0.2647 1.0000
10.250 1.1903 0.03882 0.02903 -0.0337 0.2459 1.0000
10.500 1.1895 0.04039 0.03068 -0.0312 0.2282 1.0000
10.750 1.1899 0.04212 0.03251 -0.0291 0.2116 1.0000
11.000 1.1886 0.04413 0.03462 -0.0273 0.1936 1.0000
11.250 1.1848 0.04649 0.03704 -0.0257 0.1737 1.0000
11.500 1.1799 0.04925 0.03989 -0.0245 0.1509 1.0000
11.750 1.1720 0.05250 0.04306 -0.0236 0.1294 1.0000
12.000 1.1635 0.05610 0.04659 -0.0230 0.1109 1.0000
12.250 1.1543 0.05997 0.05037 -0.0226 0.0984 1.0000
12.500 1.1448 0.06405 0.05438 -0.0226 0.0901 1.0000
12.750 1.1385 0.06792 0.05830 -0.0225 0.0830 1.0000
13.000 1.1308 0.07201 0.06238 -0.0227 0.0783 1.0000
13.250 1.1258 0.07589 0.06633 -0.0229 0.0738 1.0000
13.500 1.1217 0.07975 0.07029 -0.0232 0.0698 1.0000
13.750 1.1174 0.08363 0.07420 -0.0236 0.0667 1.0000
14.000 1.1153 0.08730 0.07793 -0.0239 0.0641 1.0000
14.250 1.1143 0.09099 0.08183 -0.0242 0.0616 1.0000
14.500 1.1128 0.09479 0.08579 -0.0248 0.0592 1.0000
14.750 1.1119 0.09845 0.08951 -0.0253 0.0571 1.0000
15.000 1.1132 0.10164 0.09266 -0.0256 0.0552 1.0000
15.250 1.1087 0.10643 0.09774 -0.0270 0.0538 1.0000
15.500 1.1031 0.11154 0.10311 -0.0288 0.0526 1.0000
15.750 1.0959 0.11711 0.10892 -0.0309 0.0517 1.0000
16.000 1.0860 0.12348 0.11552 -0.0338 0.0510 1.0000
16.250 1.0719 0.13111 0.12338 -0.0378 0.0506 1.0000
16.500 1.0505 0.14115 0.13366 -0.0436 0.0507 1.0000
16.750 1.0156 0.15622 0.14893 -0.0527 0.0514 1.0000
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Polar data table (+)
Polar graphs
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