CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 100,000 Max Cl/Cd: 53.5 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkysm-il-100000-n5.txt Download as CSV file: xf-clarkysm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3773 0.09299 0.08788 -0.0445 1.0000 0.0380
-9.250 -0.3873 0.08929 0.08427 -0.0447 1.0000 0.0378
-9.000 -0.4007 0.08564 0.08070 -0.0445 1.0000 0.0376
-8.750 -0.4185 0.08210 0.07727 -0.0439 1.0000 0.0374
-8.500 -0.4426 0.07881 0.07409 -0.0427 1.0000 0.0372
-8.250 -0.4739 0.07585 0.07125 -0.0408 1.0000 0.0367
-8.000 -0.4866 0.06384 0.05912 -0.0527 0.9909 0.0363
-7.750 -0.4970 0.05091 0.04563 -0.0622 0.9790 0.0361
-7.500 -0.4889 0.04394 0.03807 -0.0660 0.9711 0.0369
-7.250 -0.4789 0.03912 0.03263 -0.0668 0.9623 0.0385
-7.000 -0.4593 0.03447 0.02711 -0.0682 0.9570 0.0408
-6.750 -0.4386 0.03313 0.02568 -0.0679 0.9496 0.0420
-6.500 -0.4109 0.03124 0.02348 -0.0688 0.9447 0.0438
-6.250 -0.3855 0.02939 0.02121 -0.0691 0.9393 0.0465
-6.000 -0.3607 0.02783 0.01932 -0.0690 0.9328 0.0492
-5.750 -0.3287 0.02680 0.01818 -0.0703 0.9288 0.0520
-5.500 -0.3027 0.02566 0.01677 -0.0701 0.9226 0.0554
-5.250 -0.2744 0.02465 0.01562 -0.0704 0.9169 0.0594
-5.000 -0.2404 0.02377 0.01463 -0.0717 0.9132 0.0639
-4.750 -0.2141 0.02296 0.01363 -0.0714 0.9067 0.0689
-4.500 -0.1847 0.02226 0.01294 -0.0719 0.9011 0.0741
-4.250 -0.1493 0.02149 0.01203 -0.0733 0.8976 0.0815
-4.000 -0.1242 0.02095 0.01150 -0.0728 0.8904 0.0879
-3.750 -0.0934 0.02033 0.01083 -0.0734 0.8848 0.0964
-3.500 -0.0580 0.01975 0.01018 -0.0747 0.8812 0.1071
-3.250 -0.0358 0.01932 0.00982 -0.0737 0.8726 0.1169
-3.000 -0.0038 0.01878 0.00930 -0.0744 0.8675 0.1313
-2.750 0.0251 0.01834 0.00889 -0.0745 0.8613 0.1494
-2.500 0.0517 0.01792 0.00858 -0.0742 0.8539 0.1740
-2.250 0.0861 0.01740 0.00818 -0.0753 0.8495 0.2158
-2.000 0.1079 0.01709 0.00805 -0.0741 0.8401 0.2631
-1.750 0.1405 0.01657 0.00775 -0.0749 0.8347 0.3311
-1.500 0.1643 0.01617 0.00764 -0.0740 0.8258 0.4087
-1.250 0.1946 0.01548 0.00744 -0.0742 0.8196 0.5433
-1.000 0.2233 0.01482 0.00749 -0.0734 0.8117 0.7454
-0.750 0.3354 0.01447 0.00732 -0.0892 0.8091 0.9584
-0.500 0.4064 0.01426 0.00691 -0.0976 0.8020 1.0000
-0.250 0.4275 0.01424 0.00675 -0.0961 0.7889 1.0000
0.000 0.4501 0.01422 0.00660 -0.0949 0.7761 1.0000
0.250 0.4740 0.01420 0.00645 -0.0939 0.7641 1.0000
0.500 0.4998 0.01417 0.00629 -0.0933 0.7531 1.0000
0.750 0.5224 0.01420 0.00623 -0.0920 0.7407 1.0000
1.000 0.5446 0.01426 0.00621 -0.0907 0.7281 1.0000
1.250 0.5678 0.01432 0.00617 -0.0896 0.7158 1.0000
1.500 0.5918 0.01437 0.00614 -0.0886 0.7035 1.0000
1.750 0.6162 0.01443 0.00609 -0.0877 0.6910 1.0000
2.000 0.6384 0.01453 0.00613 -0.0864 0.6774 1.0000
2.250 0.6606 0.01465 0.00619 -0.0851 0.6634 1.0000
2.500 0.6830 0.01477 0.00624 -0.0838 0.6492 1.0000
2.750 0.7054 0.01490 0.00631 -0.0826 0.6346 1.0000
3.000 0.7276 0.01505 0.00639 -0.0813 0.6195 1.0000
3.250 0.7496 0.01521 0.00650 -0.0799 0.6041 1.0000
3.500 0.7714 0.01539 0.00662 -0.0786 0.5884 1.0000
3.750 0.7930 0.01558 0.00675 -0.0772 0.5722 1.0000
4.000 0.8143 0.01580 0.00692 -0.0758 0.5555 1.0000
4.250 0.8355 0.01604 0.00709 -0.0743 0.5389 1.0000
4.500 0.8565 0.01630 0.00729 -0.0729 0.5225 1.0000
4.750 0.8772 0.01658 0.00752 -0.0714 0.5061 1.0000
5.000 0.8977 0.01688 0.00778 -0.0699 0.4898 1.0000
5.250 0.9180 0.01721 0.00805 -0.0685 0.4741 1.0000
5.500 0.9384 0.01755 0.00836 -0.0670 0.4593 1.0000
5.750 0.9587 0.01792 0.00872 -0.0656 0.4454 1.0000
6.000 0.9790 0.01830 0.00908 -0.0642 0.4320 1.0000
6.250 0.9990 0.01870 0.00945 -0.0628 0.4191 1.0000
6.500 1.0181 0.01912 0.00983 -0.0612 0.4053 1.0000
6.750 1.0359 0.01955 0.01024 -0.0594 0.3902 1.0000
7.000 1.0524 0.01999 0.01064 -0.0574 0.3743 1.0000
7.250 1.0683 0.02045 0.01106 -0.0554 0.3585 1.0000
7.500 1.0842 0.02092 0.01150 -0.0533 0.3441 1.0000
7.750 1.0998 0.02140 0.01198 -0.0513 0.3309 1.0000
8.000 1.1160 0.02188 0.01251 -0.0494 0.3189 1.0000
8.250 1.1316 0.02238 0.01306 -0.0474 0.3074 1.0000
8.500 1.1457 0.02289 0.01360 -0.0452 0.2960 1.0000
8.750 1.1579 0.02344 0.01417 -0.0427 0.2848 1.0000
9.000 1.1697 0.02400 0.01479 -0.0402 0.2721 1.0000
9.250 1.1806 0.02460 0.01546 -0.0377 0.2587 1.0000
9.500 1.1905 0.02526 0.01618 -0.0351 0.2441 1.0000
9.750 1.1991 0.02601 0.01698 -0.0324 0.2279 1.0000
10.000 1.2062 0.02688 0.01785 -0.0298 0.2097 1.0000
10.250 1.2123 0.02787 0.01885 -0.0271 0.1872 1.0000
10.500 1.2152 0.02912 0.02001 -0.0244 0.1655 1.0000
10.750 1.2174 0.03054 0.02135 -0.0218 0.1473 1.0000
11.000 1.2190 0.03211 0.02287 -0.0193 0.1340 1.0000
11.250 1.2202 0.03380 0.02454 -0.0171 0.1244 1.0000
11.500 1.2214 0.03557 0.02631 -0.0150 0.1168 1.0000
11.750 1.2232 0.03737 0.02816 -0.0132 0.1109 1.0000
12.000 1.2250 0.03926 0.03011 -0.0115 0.1056 1.0000
12.250 1.2240 0.04142 0.03227 -0.0100 0.1017 1.0000
12.500 1.2278 0.04332 0.03429 -0.0087 0.0976 1.0000
12.750 1.2302 0.04537 0.03644 -0.0076 0.0938 1.0000
13.000 1.2306 0.04764 0.03876 -0.0065 0.0905 1.0000
13.250 1.2323 0.04988 0.04104 -0.0056 0.0874 1.0000
13.500 1.2364 0.05199 0.04331 -0.0048 0.0844 1.0000
13.750 1.2393 0.05423 0.04567 -0.0042 0.0814 1.0000
14.000 1.2409 0.05664 0.04813 -0.0036 0.0786 1.0000
14.250 1.2445 0.05889 0.05037 -0.0030 0.0761 1.0000
14.500 1.2470 0.06140 0.05310 -0.0027 0.0735 1.0000
14.750 1.2490 0.06401 0.05587 -0.0025 0.0709 1.0000
15.000 1.2501 0.06671 0.05867 -0.0025 0.0686 1.0000
15.250 1.2517 0.06936 0.06135 -0.0025 0.0663 1.0000
15.500 1.2537 0.07212 0.06421 -0.0025 0.0642 1.0000
15.750 1.2509 0.07562 0.06796 -0.0030 0.0621 1.0000
16.000 1.2480 0.07917 0.07168 -0.0037 0.0599 1.0000
16.250 1.2461 0.08261 0.07523 -0.0045 0.0581 1.0000
16.500 1.2457 0.08582 0.07848 -0.0052 0.0563 1.0000
16.750 1.2449 0.08919 0.08193 -0.0059 0.0546 1.0000
17.000 1.2347 0.09429 0.08731 -0.0078 0.0531 1.0000
17.250 1.2254 0.09937 0.09264 -0.0098 0.0517 1.0000
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Polar data table (+)
Polar graphs
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