S4110 (s4110-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 50,000 Max Cl/Cd: 40.79 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4110-il-50000-n5.txt Download as CSV file: xf-s4110-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3861 0.09744 0.09024 -0.0317 1.0000 0.0567
-8.250 -0.3880 0.09390 0.08679 -0.0326 1.0000 0.0548
-7.750 -0.4126 0.08542 0.07859 -0.0383 1.0000 0.0496
-7.500 -0.4112 0.08218 0.07542 -0.0385 1.0000 0.0492
-7.250 -0.4110 0.07871 0.07201 -0.0394 1.0000 0.0487
-7.000 -0.4110 0.07494 0.06830 -0.0408 1.0000 0.0483
-6.750 -0.4106 0.07097 0.06437 -0.0424 1.0000 0.0479
-6.500 -0.4093 0.06678 0.06018 -0.0441 1.0000 0.0475
-6.250 -0.4065 0.06234 0.05568 -0.0460 1.0000 0.0473
-6.000 -0.4015 0.05754 0.05073 -0.0483 1.0000 0.0475
-5.750 -0.3930 0.05254 0.04546 -0.0507 1.0000 0.0480
-5.500 -0.3800 0.04735 0.03980 -0.0532 1.0000 0.0491
-5.250 -0.3643 0.04327 0.03531 -0.0545 1.0000 0.0506
-5.000 -0.3477 0.04078 0.03265 -0.0545 1.0000 0.0522
-4.750 -0.3276 0.03767 0.02916 -0.0551 1.0000 0.0536
-4.500 -0.3053 0.03469 0.02571 -0.0556 1.0000 0.0556
-4.250 -0.2810 0.03194 0.02237 -0.0559 1.0000 0.0594
-4.000 -0.2578 0.03003 0.02011 -0.0559 1.0000 0.0653
-3.750 -0.2340 0.02843 0.01816 -0.0556 1.0000 0.0724
-3.500 -0.2110 0.02718 0.01671 -0.0552 1.0000 0.0821
-3.250 -0.1873 0.02602 0.01534 -0.0548 1.0000 0.0942
-3.000 -0.1638 0.02503 0.01419 -0.0543 1.0000 0.1076
-2.750 -0.1410 0.02427 0.01330 -0.0536 1.0000 0.1222
-2.500 -0.1175 0.02359 0.01250 -0.0531 0.9996 0.1372
-2.250 -0.0806 0.02298 0.01175 -0.0551 0.9936 0.1593
-2.000 -0.0442 0.02244 0.01120 -0.0572 0.9870 0.1903
-1.750 -0.0075 0.02183 0.01081 -0.0594 0.9807 0.2377
-1.500 0.0282 0.02107 0.01058 -0.0616 0.9739 0.3469
-1.250 0.0581 0.02019 0.01066 -0.0620 0.9672 0.5695
-1.000 0.0884 0.01923 0.01051 -0.0609 0.9582 1.0000
-0.750 0.1238 0.01949 0.01036 -0.0628 0.9489 1.0000
-0.500 0.1624 0.01978 0.01032 -0.0652 0.9407 1.0000
-0.250 0.1980 0.02004 0.01032 -0.0670 0.9311 1.0000
0.000 0.2324 0.02029 0.01035 -0.0685 0.9211 1.0000
0.250 0.2712 0.02053 0.01040 -0.0708 0.9124 1.0000
0.500 0.3061 0.02074 0.01048 -0.0723 0.9018 1.0000
0.750 0.3396 0.02096 0.01057 -0.0735 0.8907 1.0000
1.000 0.3761 0.02113 0.01066 -0.0751 0.8804 1.0000
1.250 0.4164 0.02123 0.01070 -0.0772 0.8710 1.0000
1.500 0.4484 0.02138 0.01081 -0.0778 0.8583 1.0000
1.750 0.4810 0.02148 0.01089 -0.0784 0.8454 1.0000
2.000 0.5136 0.02155 0.01096 -0.0790 0.8322 1.0000
2.250 0.5463 0.02159 0.01102 -0.0793 0.8185 1.0000
2.500 0.5785 0.02159 0.01105 -0.0795 0.8039 1.0000
2.750 0.6102 0.02155 0.01105 -0.0795 0.7885 1.0000
3.000 0.6417 0.02147 0.01104 -0.0794 0.7721 1.0000
3.250 0.6734 0.02134 0.01096 -0.0791 0.7550 1.0000
3.500 0.6998 0.02136 0.01104 -0.0781 0.7343 1.0000
3.750 0.7289 0.02126 0.01103 -0.0773 0.7134 1.0000
4.000 0.7554 0.02124 0.01106 -0.0762 0.6895 1.0000
4.250 0.7826 0.02119 0.01105 -0.0750 0.6637 1.0000
4.500 0.8085 0.02120 0.01109 -0.0737 0.6347 1.0000
4.750 0.8335 0.02129 0.01122 -0.0723 0.6021 1.0000
5.000 0.8584 0.02143 0.01131 -0.0709 0.5669 1.0000
5.250 0.8811 0.02172 0.01155 -0.0693 0.5277 1.0000
5.500 0.9030 0.02214 0.01186 -0.0677 0.4866 1.0000
5.750 0.9236 0.02271 0.01228 -0.0660 0.4444 1.0000
6.000 0.9431 0.02342 0.01288 -0.0644 0.4035 1.0000
6.250 0.9618 0.02425 0.01355 -0.0628 0.3645 1.0000
6.500 0.9803 0.02519 0.01437 -0.0613 0.3291 1.0000
6.750 0.9985 0.02620 0.01528 -0.0599 0.2970 1.0000
7.000 1.0169 0.02727 0.01631 -0.0585 0.2691 1.0000
7.250 1.0352 0.02839 0.01737 -0.0573 0.2443 1.0000
7.500 1.0540 0.02955 0.01851 -0.0561 0.2223 1.0000
7.750 1.0726 0.03076 0.01970 -0.0549 0.2027 1.0000
8.000 1.0915 0.03201 0.02102 -0.0538 0.1849 1.0000
8.250 1.1096 0.03330 0.02240 -0.0526 0.1687 1.0000
8.500 1.1279 0.03467 0.02385 -0.0515 0.1545 1.0000
8.750 1.1452 0.03610 0.02536 -0.0503 0.1411 1.0000
9.000 1.1630 0.03766 0.02704 -0.0491 0.1297 1.0000
9.250 1.1796 0.03928 0.02872 -0.0480 0.1195 1.0000
9.500 1.1943 0.04089 0.03042 -0.0466 0.1097 1.0000
9.750 1.2109 0.04296 0.03285 -0.0454 0.1014 1.0000
10.000 1.2249 0.04481 0.03472 -0.0441 0.0943 1.0000
10.250 1.2349 0.04698 0.03727 -0.0425 0.0871 1.0000
10.500 1.2488 0.04913 0.03939 -0.0413 0.0822 1.0000
10.750 1.2527 0.05199 0.04279 -0.0392 0.0772 1.0000
11.000 1.2560 0.05411 0.04507 -0.0372 0.0729 1.0000
11.250 1.2606 0.05659 0.04762 -0.0356 0.0694 1.0000
11.500 1.2535 0.06025 0.05177 -0.0334 0.0673 1.0000
11.750 1.2431 0.06402 0.05591 -0.0316 0.0654 1.0000
12.000 1.2310 0.06791 0.06009 -0.0305 0.0636 1.0000
12.250 1.2185 0.07195 0.06436 -0.0301 0.0621 1.0000
12.500 1.2090 0.07582 0.06837 -0.0302 0.0605 1.0000
12.750 1.2078 0.07900 0.07153 -0.0302 0.0584 1.0000
13.000 1.1840 0.08532 0.07813 -0.0323 0.0583 1.0000
13.250 1.1592 0.09251 0.08554 -0.0355 0.0583 1.0000
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Polar data table (+)
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