S4180-098-84 (s4180-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 200,000 Max Cl/Cd: 78.75 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4180-il-200000.txt Download as CSV file: xf-s4180-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4180-098-84
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3046 0.10061 0.09718 -0.0286 1.0000 0.0458
-8.500 -0.3087 0.09817 0.09481 -0.0327 1.0000 0.0462
-8.250 -0.3054 0.09367 0.09037 -0.0336 1.0000 0.0466
-8.000 -0.2896 0.09011 0.08681 -0.0312 1.0000 0.0474
-7.750 -0.2800 0.08745 0.08419 -0.0305 1.0000 0.0483
-7.500 -0.2745 0.08505 0.08184 -0.0305 1.0000 0.0493
-7.250 -0.2745 0.08301 0.07989 -0.0300 1.0000 0.0509
-7.000 -0.2910 0.08219 0.07921 -0.0269 1.0000 0.0514
-6.750 -0.2820 0.07900 0.07605 -0.0321 0.9917 0.0536
-6.500 -0.2386 0.06902 0.06597 -0.0590 0.9767 0.0568
-6.250 -0.2138 0.06600 0.06298 -0.0584 0.9721 0.0580
-6.000 -0.1853 0.06261 0.05957 -0.0621 0.9626 0.0598
-5.750 -0.1526 0.05817 0.05505 -0.0698 0.9512 0.0630
-5.500 -0.1147 0.04945 0.04592 -0.0866 0.9337 0.0688
-5.250 -0.0954 0.04705 0.04355 -0.0862 0.9210 0.0700
-5.000 -0.0763 0.04486 0.04132 -0.0862 0.9072 0.0720
-4.750 -0.0467 0.04074 0.03645 -0.0923 0.8917 0.0812
-4.500 -0.0299 0.03736 0.03317 -0.0916 0.8797 0.0827
-4.250 -0.0105 0.03571 0.03153 -0.0907 0.8660 0.0854
-4.000 0.0239 0.02564 0.02021 -0.0942 0.8549 0.0535
-3.750 0.0531 0.02125 0.01479 -0.0941 0.8441 0.0460
-3.500 0.0793 0.01927 0.01244 -0.0935 0.8326 0.0458
-3.250 0.1063 0.01793 0.01078 -0.0930 0.8198 0.0462
-3.000 0.1328 0.01634 0.00899 -0.0925 0.8078 0.0476
-2.750 0.1593 0.01572 0.00830 -0.0919 0.7960 0.0508
-2.500 0.1864 0.01505 0.00747 -0.0912 0.7844 0.0540
-2.250 0.2137 0.01418 0.00651 -0.0907 0.7716 0.0574
-2.000 0.2410 0.01361 0.00592 -0.0902 0.7591 0.0646
-1.750 0.2685 0.01301 0.00532 -0.0898 0.7473 0.0829
-1.500 0.2959 0.01258 0.00491 -0.0894 0.7360 0.1137
-1.250 0.3236 0.01234 0.00467 -0.0892 0.7230 0.1412
-1.000 0.3511 0.01204 0.00451 -0.0890 0.7104 0.1811
-0.750 0.3786 0.01155 0.00431 -0.0890 0.6986 0.2618
-0.500 0.4027 0.01047 0.00431 -0.0884 0.6877 0.5903
-0.250 0.4234 0.00957 0.00418 -0.0854 0.6759 1.0000
0.000 0.4516 0.00969 0.00409 -0.0852 0.6638 1.0000
0.250 0.4796 0.00983 0.00402 -0.0850 0.6525 1.0000
0.500 0.5076 0.00998 0.00396 -0.0847 0.6419 1.0000
0.750 0.5356 0.01011 0.00397 -0.0846 0.6299 1.0000
1.000 0.5636 0.01027 0.00399 -0.0844 0.6189 1.0000
1.250 0.5915 0.01044 0.00400 -0.0842 0.6090 1.0000
1.500 0.6194 0.01060 0.00406 -0.0840 0.5979 1.0000
1.750 0.6472 0.01078 0.00414 -0.0839 0.5875 1.0000
2.000 0.6750 0.01098 0.00419 -0.0837 0.5784 1.0000
2.250 0.7028 0.01114 0.00431 -0.0836 0.5676 1.0000
2.500 0.7305 0.01135 0.00443 -0.0834 0.5581 1.0000
2.750 0.7581 0.01155 0.00453 -0.0832 0.5488 1.0000
3.000 0.7857 0.01174 0.00470 -0.0831 0.5387 1.0000
3.250 0.8132 0.01197 0.00483 -0.0829 0.5298 1.0000
3.500 0.8406 0.01216 0.00499 -0.0827 0.5198 1.0000
3.750 0.8679 0.01238 0.00517 -0.0825 0.5102 1.0000
4.000 0.8952 0.01261 0.00532 -0.0823 0.5012 1.0000
4.250 0.9222 0.01280 0.00553 -0.0821 0.4907 1.0000
4.500 0.9492 0.01304 0.00572 -0.0818 0.4813 1.0000
4.750 0.9761 0.01325 0.00591 -0.0816 0.4715 1.0000
5.000 1.0028 0.01347 0.00615 -0.0813 0.4611 1.0000
5.250 1.0295 0.01372 0.00635 -0.0811 0.4516 1.0000
5.500 1.0558 0.01393 0.00658 -0.0807 0.4409 1.0000
5.750 1.0820 0.01416 0.00683 -0.0804 0.4298 1.0000
6.000 1.1080 0.01441 0.00706 -0.0801 0.4190 1.0000
6.250 1.1339 0.01466 0.00728 -0.0797 0.4078 1.0000
6.500 1.1593 0.01487 0.00756 -0.0793 0.3951 1.0000
6.750 1.1845 0.01511 0.00784 -0.0789 0.3822 1.0000
7.000 1.2094 0.01538 0.00812 -0.0785 0.3690 1.0000
7.250 1.2340 0.01567 0.00844 -0.0780 0.3552 1.0000
7.500 1.2581 0.01598 0.00877 -0.0774 0.3406 1.0000
7.750 1.2817 0.01632 0.00913 -0.0768 0.3243 1.0000
8.000 1.3046 0.01671 0.00953 -0.0762 0.3068 1.0000
8.250 1.3267 0.01719 0.00997 -0.0755 0.2883 1.0000
8.500 1.3479 0.01772 0.01050 -0.0746 0.2675 1.0000
8.750 1.3675 0.01839 0.01110 -0.0737 0.2452 1.0000
9.000 1.3859 0.01917 0.01182 -0.0726 0.2229 1.0000
9.250 1.4025 0.02008 0.01265 -0.0713 0.2020 1.0000
9.500 1.4171 0.02112 0.01358 -0.0698 0.1836 1.0000
9.750 1.4312 0.02216 0.01458 -0.0683 0.1670 1.0000
10.000 1.4431 0.02329 0.01568 -0.0665 0.1536 1.0000
10.500 1.4627 0.02558 0.01796 -0.0625 0.1334 1.0000
10.750 1.4682 0.02689 0.01925 -0.0600 0.1263 1.0000
11.000 1.4752 0.02813 0.02054 -0.0579 0.1195 1.0000
11.250 1.4800 0.02970 0.02209 -0.0559 0.1141 1.0000
11.500 1.4880 0.03104 0.02356 -0.0543 0.1089 1.0000
11.750 1.4929 0.03274 0.02523 -0.0528 0.1045 1.0000
12.000 1.4998 0.03442 0.02699 -0.0514 0.1004 1.0000
12.250 1.5068 0.03604 0.02873 -0.0502 0.0965 1.0000
12.500 1.5128 0.03785 0.03057 -0.0492 0.0931 1.0000
12.750 1.5207 0.03979 0.03248 -0.0480 0.0897 1.0000
13.000 1.5264 0.04168 0.03457 -0.0472 0.0869 1.0000
13.250 1.5320 0.04366 0.03666 -0.0465 0.0841 1.0000
13.500 1.5375 0.04569 0.03874 -0.0458 0.0814 1.0000
13.750 1.5504 0.04758 0.04055 -0.0448 0.0783 1.0000
14.000 1.5529 0.04994 0.04315 -0.0444 0.0767 1.0000
14.250 1.5558 0.05242 0.04582 -0.0441 0.0747 1.0000
14.500 1.5592 0.05490 0.04845 -0.0438 0.0726 1.0000
14.750 1.5635 0.05730 0.05092 -0.0437 0.0707 1.0000
15.000 1.5711 0.05953 0.05315 -0.0433 0.0686 1.0000
15.250 1.5774 0.06231 0.05606 -0.0428 0.0666 1.0000
15.500 1.5741 0.06568 0.05966 -0.0432 0.0656 1.0000
15.750 1.5707 0.06922 0.06342 -0.0437 0.0643 1.0000
16.000 1.5658 0.07299 0.06739 -0.0444 0.0629 1.0000
16.250 1.5620 0.07674 0.07130 -0.0454 0.0616 1.0000
16.500 1.5600 0.08024 0.07490 -0.0463 0.0601 1.0000
16.750 1.5632 0.08312 0.07781 -0.0469 0.0585 1.0000
17.000 1.5613 0.08720 0.08198 -0.0474 0.0567 1.0000
17.250 1.5468 0.09282 0.08786 -0.0500 0.0561 1.0000
17.500 1.5315 0.09886 0.09414 -0.0529 0.0554 1.0000
17.750 1.5150 0.10540 0.10092 -0.0562 0.0547 1.0000
18.000 1.4972 0.11244 0.10820 -0.0601 0.0540 1.0000
18.250 1.4774 0.12021 0.11620 -0.0646 0.0534 1.0000
18.500 1.4516 0.12945 0.12568 -0.0702 0.0532 1.0000
18.750 1.4014 0.14476 0.14130 -0.0802 0.0543 1.0000
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Polar data table (+)
Polar graphs
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