S4180-098-84 (s4180-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 100,000 Max Cl/Cd: 55.06 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4180-il-100000.txt Download as CSV file: xf-s4180-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2734 0.09322 0.08862 -0.0278 1.0000 0.0901
-7.500 -0.2791 0.09162 0.08714 -0.0297 1.0000 0.0929
-7.250 -0.2998 0.09143 0.08714 -0.0316 1.0000 0.0940
-7.000 -0.3203 0.09107 0.08693 -0.0338 1.0000 0.0945
-6.750 -0.3403 0.09050 0.08644 -0.0346 1.0000 0.0947
-6.500 -0.3439 0.08680 0.08286 -0.0290 1.0000 0.0955
-6.250 -0.3464 0.08450 0.08064 -0.0232 1.0000 0.0966
-6.000 -0.3480 0.08263 0.07883 -0.0200 0.9993 0.0980
-5.750 -0.3131 0.07825 0.07442 -0.0264 0.9911 0.1033
-5.500 -0.2678 0.07125 0.06727 -0.0466 0.9780 0.1113
-5.250 -0.2368 0.06789 0.06394 -0.0467 0.9719 0.1165
-5.000 -0.1944 0.06223 0.05813 -0.0602 0.9602 0.1279
-4.500 -0.1148 0.05395 0.04969 -0.0727 0.9436 0.1472
-4.250 -0.0629 0.05082 0.04602 -0.0854 0.9316 0.1731
-4.000 -0.0320 0.04609 0.04152 -0.0862 0.9253 0.1775
-3.750 0.0294 0.03464 0.02867 -0.0990 0.9146 0.0972
-3.500 0.0666 0.03098 0.02459 -0.1013 0.9041 0.0887
-3.250 0.1104 0.02689 0.01944 -0.1039 0.8961 0.0817
-3.000 0.1413 0.02489 0.01704 -0.1041 0.8834 0.0818
-2.750 0.1715 0.02323 0.01518 -0.1041 0.8714 0.0842
-2.500 0.2022 0.02213 0.01390 -0.1038 0.8602 0.0907
-2.250 0.2314 0.02089 0.01249 -0.1032 0.8489 0.0996
-2.000 0.2581 0.01987 0.01138 -0.1022 0.8357 0.1133
-1.750 0.2846 0.01911 0.01061 -0.1013 0.8230 0.1424
-1.500 0.3105 0.01844 0.01011 -0.1005 0.8111 0.1810
-1.250 0.3369 0.01775 0.00950 -0.0994 0.8003 0.2232
-1.000 0.3615 0.01705 0.00913 -0.0984 0.7870 0.2878
-0.750 0.3759 0.01523 0.00908 -0.0949 0.7753 0.7169
-0.500 0.4072 0.01475 0.00858 -0.0938 0.7641 1.0000
-0.250 0.4344 0.01484 0.00835 -0.0930 0.7529 1.0000
0.000 0.4609 0.01503 0.00831 -0.0924 0.7399 1.0000
0.250 0.4876 0.01522 0.00829 -0.0919 0.7277 1.0000
0.500 0.5146 0.01537 0.00822 -0.0912 0.7169 1.0000
0.750 0.5418 0.01552 0.00818 -0.0906 0.7060 1.0000
1.000 0.5684 0.01577 0.00829 -0.0902 0.6937 1.0000
1.250 0.5953 0.01599 0.00838 -0.0897 0.6827 1.0000
1.500 0.6229 0.01614 0.00834 -0.0891 0.6734 1.0000
1.750 0.6493 0.01644 0.00857 -0.0888 0.6613 1.0000
2.000 0.6761 0.01673 0.00876 -0.0884 0.6506 1.0000
2.250 0.7038 0.01690 0.00877 -0.0878 0.6418 1.0000
2.500 0.7301 0.01726 0.00910 -0.0875 0.6301 1.0000
2.750 0.7567 0.01758 0.00936 -0.0872 0.6199 1.0000
3.000 0.7844 0.01779 0.00944 -0.0867 0.6109 1.0000
3.250 0.8103 0.01819 0.00985 -0.0864 0.5996 1.0000
3.500 0.8370 0.01851 0.01012 -0.0860 0.5898 1.0000
3.750 0.8643 0.01876 0.01029 -0.0855 0.5804 1.0000
4.000 0.8900 0.01916 0.01073 -0.0851 0.5692 1.0000
4.250 0.9167 0.01946 0.01098 -0.0847 0.5596 1.0000
4.500 0.9435 0.01972 0.01119 -0.0842 0.5494 1.0000
4.750 0.9689 0.02012 0.01164 -0.0837 0.5379 1.0000
5.000 0.9952 0.02042 0.01191 -0.0832 0.5276 1.0000
5.250 1.0222 0.02063 0.01205 -0.0827 0.5173 1.0000
5.500 1.0470 0.02101 0.01252 -0.0821 0.5051 1.0000
5.750 1.0724 0.02133 0.01286 -0.0816 0.4935 1.0000
6.000 1.0989 0.02156 0.01304 -0.0810 0.4824 1.0000
6.250 1.1249 0.02177 0.01322 -0.0804 0.4705 1.0000
6.500 1.1493 0.02208 0.01362 -0.0797 0.4571 1.0000
6.750 1.1737 0.02236 0.01394 -0.0790 0.4435 1.0000
7.000 1.1982 0.02261 0.01422 -0.0782 0.4296 1.0000
7.250 1.2223 0.02284 0.01449 -0.0775 0.4151 1.0000
7.500 1.2460 0.02307 0.01474 -0.0766 0.3999 1.0000
7.750 1.2690 0.02332 0.01501 -0.0757 0.3839 1.0000
8.000 1.2915 0.02357 0.01527 -0.0747 0.3668 1.0000
8.250 1.3133 0.02386 0.01557 -0.0737 0.3492 1.0000
8.500 1.3340 0.02423 0.01590 -0.0725 0.3306 1.0000
8.750 1.3519 0.02476 0.01653 -0.0712 0.3093 1.0000
9.000 1.3699 0.02535 0.01707 -0.0698 0.2885 1.0000
9.250 1.3856 0.02618 0.01787 -0.0683 0.2667 1.0000
9.500 1.4001 0.02714 0.01877 -0.0667 0.2459 1.0000
9.750 1.4143 0.02830 0.01976 -0.0651 0.2274 1.0000
10.000 1.4266 0.02959 0.02105 -0.0634 0.2098 1.0000
10.250 1.4390 0.03096 0.02239 -0.0617 0.1948 1.0000
10.500 1.4522 0.03242 0.02378 -0.0602 0.1821 1.0000
10.750 1.4674 0.03392 0.02515 -0.0590 0.1708 1.0000
11.000 1.4769 0.03542 0.02682 -0.0571 0.1611 1.0000
11.250 1.4911 0.03709 0.02849 -0.0559 0.1528 1.0000
11.500 1.5058 0.03864 0.03006 -0.0547 0.1452 1.0000
11.750 1.5182 0.04052 0.03206 -0.0533 0.1388 1.0000
12.000 1.5289 0.04213 0.03375 -0.0518 0.1328 1.0000
12.250 1.5482 0.04420 0.03583 -0.0513 0.1272 1.0000
12.500 1.5496 0.04619 0.03811 -0.0490 0.1232 1.0000
12.750 1.5622 0.04798 0.03995 -0.0479 0.1186 1.0000
13.000 1.5778 0.05046 0.04249 -0.0474 0.1144 1.0000
13.250 1.5711 0.05294 0.04530 -0.0450 0.1119 1.0000
13.500 1.5679 0.05560 0.04822 -0.0433 0.1093 1.0000
13.750 1.5693 0.05814 0.05093 -0.0422 0.1066 1.0000
14.000 1.5948 0.06086 0.05355 -0.0423 0.1025 1.0000
14.250 1.5747 0.06438 0.05743 -0.0406 0.1016 1.0000
14.500 1.5533 0.06858 0.06197 -0.0398 0.1007 1.0000
14.750 1.5299 0.07348 0.06719 -0.0399 0.0999 1.0000
15.000 1.5030 0.07925 0.07327 -0.0409 0.0994 1.0000
15.250 1.4706 0.08625 0.08057 -0.0431 0.0992 1.0000
15.500 1.4300 0.09508 0.08969 -0.0469 0.0996 1.0000
15.750 1.3790 0.10671 0.10159 -0.0532 0.1006 1.0000
16.000 1.3183 0.12198 0.11706 -0.0623 0.1021 1.0000
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Polar data table (+)
Polar graphs
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