S4110 (s4110-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 50,000 Max Cl/Cd: 39.24 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4110-il-50000.txt Download as CSV file: xf-s4110-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4022 0.10652 0.09968 -0.0240 1.0000 0.2053
-8.000 -0.3727 0.10025 0.09335 -0.0218 1.0000 0.2154
-7.750 -0.4010 0.10090 0.09424 -0.0226 1.0000 0.2199
-7.500 -0.3756 0.09544 0.08874 -0.0207 1.0000 0.2317
-7.250 -0.3741 0.09253 0.08592 -0.0196 1.0000 0.2399
-7.000 -0.3929 0.09193 0.08551 -0.0184 1.0000 0.2485
-6.750 -0.3861 0.08871 0.08235 -0.0164 1.0000 0.2618
-6.500 -0.3830 0.08585 0.07957 -0.0145 1.0000 0.2742
-6.250 -0.3840 0.08336 0.07719 -0.0128 1.0000 0.2872
-6.000 -0.3864 0.08102 0.07495 -0.0109 1.0000 0.3015
-5.750 -0.3893 0.07870 0.07271 -0.0089 1.0000 0.3156
-5.500 -0.3917 0.07641 0.07051 -0.0067 1.0000 0.3314
-5.250 -0.3966 0.07437 0.06858 -0.0047 1.0000 0.3497
-4.750 -0.3973 0.06954 0.06391 0.0013 1.0000 0.3891
-4.500 -0.4010 0.06746 0.06191 0.0043 1.0000 0.4152
-4.250 -0.3210 0.04620 0.03906 -0.0474 1.0000 0.1510
-4.000 -0.2917 0.04095 0.03318 -0.0508 1.0000 0.1394
-3.750 -0.2644 0.03727 0.02896 -0.0526 1.0000 0.1420
-3.500 -0.2342 0.03377 0.02472 -0.0542 1.0000 0.1449
-3.250 -0.2090 0.03144 0.02212 -0.0544 1.0000 0.1573
-3.000 -0.1819 0.02929 0.01959 -0.0547 1.0000 0.1727
-2.750 -0.1541 0.02750 0.01736 -0.0548 1.0000 0.1909
-2.500 -0.1300 0.02612 0.01596 -0.0543 1.0000 0.2119
-2.250 -0.1042 0.02498 0.01454 -0.0540 1.0000 0.2345
-2.000 -0.0807 0.02396 0.01358 -0.0533 1.0000 0.2597
-1.750 -0.0560 0.02310 0.01274 -0.0527 1.0000 0.2963
-1.500 -0.0304 0.02216 0.01205 -0.0523 1.0000 0.3575
-1.250 -0.0083 0.02013 0.01162 -0.0503 1.0000 0.6037
-1.000 0.0029 0.01896 0.01088 -0.0460 1.0000 1.0000
-0.750 0.0262 0.01932 0.01075 -0.0461 1.0000 1.0000
-0.500 0.0483 0.01972 0.01080 -0.0459 1.0000 1.0000
-0.250 0.0698 0.02016 0.01093 -0.0458 1.0000 1.0000
0.000 0.0908 0.02065 0.01118 -0.0456 1.0000 1.0000
0.250 0.1114 0.02118 0.01150 -0.0454 1.0000 1.0000
0.500 0.1316 0.02176 0.01190 -0.0453 1.0000 1.0000
0.750 0.1512 0.02238 0.01236 -0.0452 1.0000 1.0000
1.000 0.1705 0.02306 0.01292 -0.0451 1.0000 1.0000
1.250 0.1894 0.02380 0.01355 -0.0450 1.0000 1.0000
1.500 0.2079 0.02460 0.01426 -0.0450 1.0000 1.0000
1.750 0.2422 0.02578 0.01535 -0.0480 0.9920 1.0000
2.000 0.2947 0.02721 0.01673 -0.0541 0.9737 1.0000
2.250 0.3462 0.02850 0.01799 -0.0598 0.9549 1.0000
2.500 0.3915 0.02951 0.01901 -0.0640 0.9343 1.0000
2.750 0.4454 0.03050 0.02003 -0.0693 0.9144 1.0000
3.000 0.4852 0.03120 0.02081 -0.0720 0.8916 1.0000
3.250 0.5416 0.03170 0.02142 -0.0767 0.8703 1.0000
3.500 0.5803 0.03209 0.02192 -0.0784 0.8457 1.0000
3.750 0.6277 0.03216 0.02217 -0.0808 0.8218 1.0000
4.000 0.6893 0.03147 0.02170 -0.0844 0.7987 1.0000
4.250 0.7351 0.03081 0.02128 -0.0851 0.7722 1.0000
4.500 0.7817 0.02974 0.02040 -0.0852 0.7453 1.0000
4.750 0.8275 0.02835 0.01921 -0.0846 0.7165 1.0000
5.000 0.8714 0.02680 0.01786 -0.0832 0.6845 1.0000
5.250 0.9050 0.02580 0.01693 -0.0808 0.6459 1.0000
5.500 0.9360 0.02504 0.01614 -0.0782 0.6018 1.0000
5.750 0.9639 0.02473 0.01569 -0.0756 0.5528 1.0000
6.000 0.9858 0.02512 0.01586 -0.0729 0.5003 1.0000
6.250 1.0085 0.02584 0.01624 -0.0706 0.4508 1.0000
6.500 1.0293 0.02695 0.01709 -0.0686 0.4054 1.0000
6.750 1.0499 0.02825 0.01820 -0.0668 0.3658 1.0000
7.000 1.0715 0.02974 0.01956 -0.0654 0.3321 1.0000
7.250 1.0925 0.03130 0.02106 -0.0640 0.3024 1.0000
7.500 1.1156 0.03300 0.02258 -0.0629 0.2766 1.0000
7.750 1.1339 0.03481 0.02459 -0.0613 0.2534 1.0000
8.000 1.1568 0.03680 0.02646 -0.0604 0.2331 1.0000
8.250 1.1733 0.03895 0.02893 -0.0587 0.2147 1.0000
8.500 1.1915 0.04148 0.03167 -0.0573 0.1998 1.0000
8.750 1.2074 0.04390 0.03430 -0.0558 0.1851 1.0000
9.000 1.2239 0.04687 0.03747 -0.0544 0.1743 1.0000
9.250 1.2428 0.04970 0.04032 -0.0533 0.1630 1.0000
9.500 1.2406 0.05330 0.04465 -0.0503 0.1560 1.0000
9.750 1.2571 0.05676 0.04815 -0.0492 0.1485 1.0000
10.000 1.2467 0.06140 0.05349 -0.0463 0.1460 1.0000
10.250 1.2334 0.06609 0.05865 -0.0437 0.1437 1.0000
10.500 1.2167 0.07085 0.06375 -0.0414 0.1421 1.0000
10.750 1.2076 0.07487 0.06795 -0.0397 0.1387 1.0000
11.000 1.1900 0.07937 0.07261 -0.0379 0.1376 1.0000
11.250 1.1743 0.08423 0.07758 -0.0368 0.1365 1.0000
11.500 0.9920 0.11622 0.10940 -0.0601 0.1797 1.0000
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Polar data table (+)
Polar graphs
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