S4110 (s4110-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 200,000 Max Cl/Cd: 81.44 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4110-il-200000.txt Download as CSV file: xf-s4110-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4110
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4047 0.09123 0.08781 -0.0375 1.0000 0.0497
-8.000 -0.4121 0.08831 0.08497 -0.0386 1.0000 0.0498
-7.750 -0.4195 0.08308 0.07981 -0.0389 1.0000 0.0503
-7.500 -0.4160 0.08035 0.07711 -0.0349 1.0000 0.0511
-7.250 -0.4162 0.07803 0.07484 -0.0332 1.0000 0.0517
-7.000 -0.4184 0.07582 0.07267 -0.0318 1.0000 0.0525
-6.750 -0.4228 0.07344 0.07033 -0.0310 1.0000 0.0532
-6.500 -0.4272 0.07087 0.06779 -0.0308 1.0000 0.0540
-6.250 -0.4299 0.06795 0.06489 -0.0313 1.0000 0.0548
-6.000 -0.4298 0.06463 0.06157 -0.0327 1.0000 0.0562
-5.750 -0.4252 0.06049 0.05736 -0.0355 1.0000 0.0584
-5.500 -0.3873 0.04944 0.04573 -0.0512 0.9956 0.0635
-5.250 -0.3524 0.03474 0.03013 -0.0587 0.9924 0.0375
-5.000 -0.3189 0.02853 0.02330 -0.0627 0.9888 0.0350
-4.750 -0.2819 0.02454 0.01862 -0.0656 0.9858 0.0355
-4.500 -0.2428 0.02208 0.01560 -0.0681 0.9833 0.0372
-4.250 -0.2097 0.02003 0.01311 -0.0692 0.9786 0.0379
-4.000 -0.1739 0.01795 0.01071 -0.0708 0.9751 0.0401
-3.750 -0.1354 0.01693 0.00963 -0.0730 0.9719 0.0455
-3.500 -0.1005 0.01603 0.00869 -0.0745 0.9672 0.0563
-3.250 -0.0648 0.01545 0.00802 -0.0760 0.9619 0.0761
-3.000 -0.0254 0.01498 0.00760 -0.0786 0.9583 0.0950
-2.750 0.0087 0.01463 0.00727 -0.0800 0.9526 0.1115
-2.500 0.0449 0.01412 0.00679 -0.0816 0.9473 0.1277
-2.250 0.0857 0.01352 0.00629 -0.0843 0.9440 0.1524
-2.000 0.1190 0.01296 0.00596 -0.0855 0.9378 0.2004
-1.750 0.1558 0.01207 0.00573 -0.0877 0.9329 0.3553
-1.500 0.1941 0.01120 0.00563 -0.0898 0.9297 0.5727
-1.250 0.2192 0.01067 0.00563 -0.0885 0.9220 0.7282
-1.000 0.2537 0.01011 0.00547 -0.0884 0.9177 0.9189
-0.750 0.3077 0.00984 0.00507 -0.0934 0.9148 1.0000
-0.500 0.3372 0.00978 0.00491 -0.0934 0.9052 1.0000
-0.250 0.3749 0.00960 0.00461 -0.0949 0.8995 1.0000
0.000 0.4021 0.00956 0.00449 -0.0944 0.8884 1.0000
0.250 0.4310 0.00951 0.00436 -0.0942 0.8783 1.0000
0.500 0.4617 0.00941 0.00418 -0.0942 0.8691 1.0000
0.750 0.4892 0.00937 0.00406 -0.0937 0.8574 1.0000
1.000 0.5157 0.00935 0.00398 -0.0929 0.8446 1.0000
1.250 0.5424 0.00934 0.00392 -0.0922 0.8318 1.0000
1.500 0.5691 0.00934 0.00387 -0.0915 0.8184 1.0000
1.750 0.5957 0.00935 0.00382 -0.0908 0.8042 1.0000
2.000 0.6221 0.00936 0.00378 -0.0901 0.7889 1.0000
2.250 0.6483 0.00939 0.00375 -0.0893 0.7727 1.0000
2.500 0.6747 0.00943 0.00374 -0.0885 0.7556 1.0000
2.750 0.7003 0.00949 0.00376 -0.0877 0.7361 1.0000
3.000 0.7259 0.00957 0.00378 -0.0868 0.7149 1.0000
3.250 0.7513 0.00967 0.00381 -0.0860 0.6920 1.0000
3.500 0.7766 0.00980 0.00388 -0.0851 0.6677 1.0000
3.750 0.8013 0.00997 0.00397 -0.0842 0.6401 1.0000
4.000 0.8256 0.01018 0.00408 -0.0832 0.6098 1.0000
4.250 0.8494 0.01043 0.00423 -0.0822 0.5748 1.0000
4.500 0.8724 0.01077 0.00443 -0.0810 0.5369 1.0000
4.750 0.8947 0.01117 0.00466 -0.0798 0.4942 1.0000
5.000 0.9163 0.01165 0.00495 -0.0786 0.4485 1.0000
5.250 0.9373 0.01220 0.00529 -0.0773 0.4015 1.0000
5.500 0.9578 0.01282 0.00571 -0.0760 0.3551 1.0000
5.750 0.9782 0.01349 0.00617 -0.0748 0.3122 1.0000
6.000 0.9986 0.01419 0.00668 -0.0736 0.2739 1.0000
6.250 1.0193 0.01489 0.00722 -0.0725 0.2403 1.0000
6.500 1.0400 0.01560 0.00780 -0.0715 0.2128 1.0000
6.750 1.0604 0.01635 0.00843 -0.0704 0.1906 1.0000
7.000 1.0818 0.01702 0.00907 -0.0694 0.1709 1.0000
7.250 1.1026 0.01773 0.00973 -0.0684 0.1542 1.0000
7.500 1.1231 0.01848 0.01044 -0.0673 0.1398 1.0000
7.750 1.1434 0.01924 0.01121 -0.0662 0.1264 1.0000
8.000 1.1632 0.02004 0.01201 -0.0650 0.1140 1.0000
8.250 1.1823 0.02093 0.01290 -0.0638 0.1029 1.0000
8.500 1.2006 0.02191 0.01386 -0.0624 0.0929 1.0000
8.750 1.2185 0.02286 0.01480 -0.0611 0.0838 1.0000
9.000 1.2373 0.02377 0.01583 -0.0598 0.0760 1.0000
9.250 1.2535 0.02505 0.01710 -0.0583 0.0692 1.0000
9.500 1.2715 0.02583 0.01802 -0.0569 0.0629 1.0000
9.750 1.2865 0.02734 0.01952 -0.0553 0.0575 1.0000
10.000 1.3027 0.02822 0.02057 -0.0537 0.0526 1.0000
10.250 1.3159 0.02974 0.02205 -0.0521 0.0482 1.0000
10.500 1.3291 0.03107 0.02360 -0.0501 0.0446 1.0000
10.750 1.3402 0.03222 0.02490 -0.0480 0.0413 1.0000
11.000 1.3509 0.03403 0.02672 -0.0462 0.0385 1.0000
11.250 1.3619 0.03646 0.02939 -0.0443 0.0363 1.0000
11.500 1.3690 0.03806 0.03122 -0.0420 0.0342 1.0000
11.750 1.3741 0.03963 0.03294 -0.0397 0.0323 1.0000
12.000 1.3789 0.04124 0.03462 -0.0377 0.0306 1.0000
12.250 1.3822 0.04486 0.03838 -0.0361 0.0290 1.0000
12.500 1.3780 0.04803 0.04187 -0.0339 0.0284 1.0000
12.750 1.3729 0.05080 0.04493 -0.0319 0.0279 1.0000
13.000 1.3649 0.05406 0.04849 -0.0303 0.0273 1.0000
13.250 1.3542 0.05783 0.05254 -0.0293 0.0269 1.0000
13.500 1.3407 0.06212 0.05710 -0.0289 0.0267 1.0000
13.750 1.3249 0.06692 0.06217 -0.0292 0.0264 1.0000
14.000 1.3063 0.07246 0.06797 -0.0305 0.0263 1.0000
14.250 1.2855 0.07875 0.07450 -0.0329 0.0263 1.0000
14.500 1.2620 0.08606 0.08205 -0.0364 0.0264 1.0000
14.750 1.2363 0.09447 0.09069 -0.0413 0.0267 1.0000
15.000 1.2085 0.10423 0.10066 -0.0475 0.0271 1.0000
15.250 1.1784 0.11556 0.11217 -0.0552 0.0276 1.0000
15.500 1.1450 0.12888 0.12563 -0.0642 0.0282 1.0000
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Polar data table (+)
Polar graphs
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