S4061-096-84 (s4061-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 100,000 Max Cl/Cd: 60.75 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4061-il-100000-n5.txt Download as CSV file: xf-s4061-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3294 0.09012 0.08541 -0.0396 1.0000 0.0301
-8.250 -0.3263 0.08732 0.08267 -0.0399 1.0000 0.0294
-8.000 -0.3283 0.08455 0.08000 -0.0400 1.0000 0.0287
-7.750 -0.3398 0.08246 0.07804 -0.0386 1.0000 0.0282
-7.500 -0.3423 0.07933 0.07498 -0.0405 0.9913 0.0275
-7.250 -0.3283 0.06603 0.06163 -0.0599 0.9744 0.0244
-7.000 -0.3075 0.05993 0.05546 -0.0683 0.9640 0.0241
-6.750 -0.2866 0.05240 0.04774 -0.0774 0.9537 0.0237
-6.500 -0.2656 0.04467 0.03963 -0.0857 0.9441 0.0233
-6.250 -0.2471 0.03838 0.03279 -0.0905 0.9333 0.0230
-6.000 -0.2261 0.03345 0.02720 -0.0931 0.9241 0.0230
-5.750 -0.2008 0.02958 0.02264 -0.0947 0.9170 0.0233
-5.500 -0.1769 0.02689 0.01937 -0.0949 0.9085 0.0238
-5.250 -0.1494 0.02498 0.01708 -0.0954 0.9022 0.0252
-5.000 -0.1241 0.02390 0.01582 -0.0954 0.8943 0.0275
-4.750 -0.0965 0.02245 0.01404 -0.0953 0.8880 0.0294
-4.500 -0.0706 0.02116 0.01250 -0.0949 0.8806 0.0310
-4.250 -0.0443 0.02013 0.01138 -0.0946 0.8738 0.0336
-4.000 -0.0180 0.01930 0.01037 -0.0942 0.8670 0.0384
-3.750 0.0081 0.01854 0.00956 -0.0939 0.8598 0.0480
-3.500 0.0348 0.01772 0.00877 -0.0936 0.8537 0.0670
-3.250 0.0607 0.01725 0.00838 -0.0934 0.8459 0.1023
-3.000 0.0881 0.01679 0.00797 -0.0932 0.8405 0.1368
-2.750 0.1135 0.01646 0.00766 -0.0928 0.8322 0.1681
-2.500 0.1406 0.01610 0.00731 -0.0924 0.8264 0.2041
-2.250 0.1663 0.01581 0.00711 -0.0921 0.8185 0.2455
-2.000 0.1929 0.01549 0.00688 -0.0917 0.8123 0.2963
-1.750 0.2188 0.01520 0.00673 -0.0913 0.8050 0.3574
-1.500 0.2445 0.01487 0.00659 -0.0907 0.7982 0.4346
-1.250 0.2695 0.01450 0.00651 -0.0900 0.7914 0.5343
-1.000 0.2919 0.01407 0.00647 -0.0883 0.7841 0.6638
-0.750 0.3182 0.01350 0.00631 -0.0866 0.7785 0.8663
-0.500 0.3586 0.01342 0.00611 -0.0890 0.7706 1.0000
-0.250 0.3859 0.01345 0.00593 -0.0886 0.7647 1.0000
0.000 0.4119 0.01359 0.00594 -0.0883 0.7558 1.0000
0.250 0.4393 0.01363 0.00581 -0.0879 0.7498 1.0000
0.500 0.4654 0.01378 0.00587 -0.0876 0.7408 1.0000
0.750 0.4928 0.01383 0.00578 -0.0873 0.7347 1.0000
1.000 0.5189 0.01399 0.00588 -0.0870 0.7255 1.0000
1.250 0.5461 0.01406 0.00584 -0.0866 0.7188 1.0000
1.500 0.5724 0.01421 0.00594 -0.0863 0.7096 1.0000
1.750 0.5993 0.01431 0.00597 -0.0859 0.7019 1.0000
2.000 0.6259 0.01443 0.00605 -0.0855 0.6931 1.0000
2.250 0.6523 0.01456 0.00616 -0.0852 0.6842 1.0000
2.500 0.6794 0.01464 0.00617 -0.0848 0.6758 1.0000
2.750 0.7053 0.01479 0.00632 -0.0844 0.6649 1.0000
3.000 0.7317 0.01490 0.00642 -0.0839 0.6545 1.0000
3.250 0.7585 0.01498 0.00646 -0.0834 0.6444 1.0000
3.500 0.7844 0.01512 0.00661 -0.0829 0.6324 1.0000
3.750 0.8102 0.01527 0.00678 -0.0825 0.6203 1.0000
4.000 0.8362 0.01541 0.00696 -0.0820 0.6080 1.0000
4.250 0.8621 0.01556 0.00711 -0.0814 0.5953 1.0000
4.500 0.8878 0.01572 0.00728 -0.0809 0.5820 1.0000
4.750 0.9133 0.01589 0.00748 -0.0803 0.5677 1.0000
5.000 0.9385 0.01609 0.00772 -0.0797 0.5526 1.0000
5.250 0.9633 0.01630 0.00798 -0.0791 0.5363 1.0000
5.500 0.9879 0.01654 0.00824 -0.0784 0.5189 1.0000
5.750 1.0121 0.01680 0.00854 -0.0777 0.5003 1.0000
6.000 1.0358 0.01709 0.00884 -0.0769 0.4802 1.0000
6.250 1.0588 0.01743 0.00921 -0.0760 0.4577 1.0000
6.500 1.0811 0.01782 0.00959 -0.0751 0.4338 1.0000
6.750 1.1026 0.01828 0.01004 -0.0741 0.4081 1.0000
7.000 1.1232 0.01882 0.01054 -0.0730 0.3803 1.0000
7.250 1.1426 0.01943 0.01110 -0.0718 0.3512 1.0000
7.500 1.1609 0.02014 0.01174 -0.0705 0.3218 1.0000
7.750 1.1780 0.02093 0.01248 -0.0691 0.2929 1.0000
8.000 1.1942 0.02179 0.01327 -0.0676 0.2653 1.0000
8.250 1.2095 0.02270 0.01414 -0.0661 0.2401 1.0000
8.500 1.2236 0.02369 0.01506 -0.0645 0.2176 1.0000
8.750 1.2375 0.02466 0.01604 -0.0629 0.1961 1.0000
9.000 1.2496 0.02573 0.01711 -0.0611 0.1773 1.0000
9.250 1.2606 0.02681 0.01820 -0.0592 0.1595 1.0000
9.500 1.2692 0.02795 0.01936 -0.0570 0.1425 1.0000
9.750 1.2755 0.02928 0.02063 -0.0548 0.1241 1.0000
10.000 1.2814 0.03072 0.02203 -0.0529 0.1057 1.0000
10.250 1.2870 0.03226 0.02353 -0.0511 0.0891 1.0000
10.500 1.2919 0.03395 0.02523 -0.0494 0.0759 1.0000
10.750 1.2963 0.03575 0.02708 -0.0478 0.0658 1.0000
11.000 1.2990 0.03778 0.02914 -0.0462 0.0573 1.0000
11.500 1.3017 0.04233 0.03382 -0.0437 0.0437 1.0000
11.750 1.2996 0.04506 0.03659 -0.0426 0.0398 1.0000
12.000 1.2996 0.04772 0.03942 -0.0417 0.0363 1.0000
12.250 1.2977 0.05066 0.04248 -0.0410 0.0339 1.0000
12.500 1.2930 0.05401 0.04589 -0.0406 0.0323 1.0000
12.750 1.2923 0.05706 0.04915 -0.0402 0.0307 1.0000
13.000 1.2913 0.06024 0.05250 -0.0399 0.0293 1.0000
13.250 1.2897 0.06356 0.05597 -0.0399 0.0279 1.0000
13.500 1.2873 0.06706 0.05960 -0.0403 0.0267 1.0000
13.750 1.2835 0.07083 0.06347 -0.0408 0.0258 1.0000
14.000 1.2803 0.07465 0.06739 -0.0413 0.0250 1.0000
14.250 1.2788 0.07847 0.07145 -0.0419 0.0241 1.0000
14.500 1.2762 0.08253 0.07572 -0.0427 0.0234 1.0000
14.750 1.2729 0.08680 0.08019 -0.0437 0.0228 1.0000
15.000 1.2686 0.09136 0.08495 -0.0450 0.0223 1.0000
15.250 1.2630 0.09628 0.09007 -0.0466 0.0220 1.0000
15.500 1.2564 0.10150 0.09549 -0.0486 0.0217 1.0000
15.750 1.2485 0.10713 0.10132 -0.0511 0.0214 1.0000
16.000 1.2391 0.11325 0.10763 -0.0540 0.0212 1.0000
16.250 1.2281 0.11995 0.11453 -0.0575 0.0211 1.0000
16.500 1.2150 0.12739 0.12218 -0.0618 0.0210 1.0000
16.750 1.1993 0.13586 0.13086 -0.0669 0.0210 1.0000
17.000 1.1787 0.14618 0.14141 -0.0734 0.0212 1.0000
17.250 1.1470 0.16076 0.15621 -0.0830 0.0217 1.0000
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