S4180-098-84 (s4180-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 50,000 Max Cl/Cd: 28.35 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4180-il-50000.txt Download as CSV file: xf-s4180-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2839 0.10484 0.09823 -0.0214 1.0000 0.1803
-8.000 -0.2870 0.10353 0.09703 -0.0227 1.0000 0.1873
-7.750 -0.3118 0.10500 0.09873 -0.0249 1.0000 0.1893
-7.500 -0.2724 0.09715 0.09081 -0.0224 1.0000 0.1986
-7.250 -0.2897 0.09729 0.09116 -0.0231 1.0000 0.2045
-7.000 -0.2758 0.09293 0.08686 -0.0220 1.0000 0.2101
-6.750 -0.2796 0.09133 0.08540 -0.0205 1.0000 0.2177
-6.500 -0.3112 0.09254 0.08686 -0.0202 1.0000 0.2213
-6.250 -0.2956 0.08804 0.08242 -0.0163 1.0000 0.2278
-6.000 -0.3110 0.08738 0.08190 -0.0139 1.0000 0.2343
-5.750 -0.3452 0.08881 0.08350 -0.0155 1.0000 0.2379
-5.250 -0.3525 0.08444 0.07931 -0.0097 1.0000 0.2531
-5.000 -0.3543 0.08179 0.07676 -0.0062 1.0000 0.2586
-4.750 -0.3662 0.08107 0.07610 -0.0090 1.0000 0.2709
-4.500 -0.3638 0.07831 0.07343 -0.0033 1.0000 0.2779
-4.250 -0.3677 0.07644 0.07163 -0.0031 1.0000 0.2910
-4.000 -0.3689 0.07454 0.06979 -0.0023 1.0000 0.3067
-3.750 -0.3687 0.07260 0.06792 -0.0005 1.0000 0.3243
-3.500 -0.3678 0.07078 0.06615 0.0012 1.0000 0.3449
-3.250 -0.3371 0.06822 0.06357 -0.0032 0.9887 0.3992
-3.000 -0.3133 0.06494 0.06035 -0.0003 0.9782 0.4383
-2.750 -0.1239 0.04836 0.04174 -0.0641 0.9657 0.1900
-2.500 -0.0549 0.04251 0.03501 -0.0740 0.9567 0.1550
-2.250 -0.0062 0.03944 0.03145 -0.0792 0.9448 0.1522
-2.000 0.0430 0.03683 0.02821 -0.0837 0.9330 0.1504
-1.750 0.0923 0.03494 0.02567 -0.0878 0.9215 0.1586
-1.500 0.1423 0.03337 0.02388 -0.0917 0.9104 0.1777
-1.250 0.1815 0.03230 0.02268 -0.0937 0.8974 0.2099
-1.000 0.2176 0.03149 0.02184 -0.0951 0.8847 0.2560
-0.750 0.2577 0.03064 0.02115 -0.0969 0.8727 0.3224
-0.500 0.2997 0.02807 0.02049 -0.0978 0.8642 0.6360
-0.250 0.3331 0.02791 0.02002 -0.0976 0.8504 1.0000
0.000 0.3647 0.02859 0.02027 -0.0985 0.8368 1.0000
0.250 0.3966 0.02927 0.02064 -0.0995 0.8239 1.0000
0.500 0.4321 0.02986 0.02094 -0.1007 0.8120 1.0000
0.750 0.4696 0.03034 0.02118 -0.1020 0.8007 1.0000
1.000 0.4910 0.03123 0.02191 -0.1015 0.7873 1.0000
1.250 0.5151 0.03211 0.02263 -0.1013 0.7748 1.0000
1.500 0.5450 0.03281 0.02319 -0.1016 0.7638 1.0000
1.750 0.5786 0.03330 0.02355 -0.1021 0.7532 1.0000
2.000 0.5954 0.03451 0.02467 -0.1013 0.7404 1.0000
2.250 0.6169 0.03556 0.02564 -0.1009 0.7287 1.0000
2.500 0.6568 0.03570 0.02569 -0.1014 0.7201 1.0000
2.750 0.6707 0.03716 0.02711 -0.1006 0.7073 1.0000
3.000 0.6863 0.03860 0.02853 -0.0998 0.6952 1.0000
3.250 0.7117 0.03951 0.02940 -0.0995 0.6849 1.0000
3.500 0.7418 0.04008 0.02994 -0.0992 0.6746 1.0000
3.750 0.7519 0.04198 0.03184 -0.0983 0.6621 1.0000
4.000 0.7687 0.04345 0.03333 -0.0976 0.6505 1.0000
4.250 0.8117 0.04307 0.03295 -0.0974 0.6420 1.0000
4.500 0.8179 0.04532 0.03522 -0.0964 0.6286 1.0000
4.750 0.8260 0.04750 0.03742 -0.0956 0.6160 1.0000
5.000 0.8442 0.04892 0.03890 -0.0948 0.6041 1.0000
5.250 0.8925 0.04781 0.03783 -0.0940 0.5949 1.0000
5.500 0.8970 0.05032 0.04038 -0.0931 0.5810 1.0000
5.750 0.9018 0.05285 0.04296 -0.0921 0.5674 1.0000
6.000 0.9093 0.05510 0.04528 -0.0911 0.5541 1.0000
6.250 0.9253 0.05662 0.04686 -0.0900 0.5412 1.0000
6.500 0.9666 0.05578 0.04612 -0.0886 0.5289 1.0000
6.750 1.0162 0.05368 0.04416 -0.0867 0.5170 1.0000
7.000 1.0260 0.05560 0.04616 -0.0854 0.5022 1.0000
7.250 1.0392 0.05710 0.04775 -0.0839 0.4873 1.0000
7.500 1.0530 0.05851 0.04925 -0.0824 0.4724 1.0000
7.750 1.0752 0.05887 0.04975 -0.0806 0.4574 1.0000
8.000 1.1085 0.05788 0.04887 -0.0784 0.4421 1.0000
8.250 1.1677 0.05372 0.04486 -0.0757 0.4259 1.0000
8.500 1.2447 0.04769 0.03878 -0.0736 0.4075 1.0000
8.750 1.2492 0.04962 0.04088 -0.0716 0.3894 1.0000
9.000 1.2655 0.05019 0.04157 -0.0695 0.3705 1.0000
9.250 1.3157 0.04721 0.03848 -0.0679 0.3486 1.0000
9.500 1.3388 0.04723 0.03849 -0.0661 0.3289 1.0000
9.750 1.3504 0.04850 0.03989 -0.0641 0.3108 1.0000
10.000 1.3686 0.04923 0.04063 -0.0624 0.2928 1.0000
10.250 1.3868 0.05021 0.04162 -0.0608 0.2764 1.0000
10.500 1.3997 0.05173 0.04319 -0.0591 0.2618 1.0000
10.750 1.4055 0.05405 0.04564 -0.0573 0.2499 1.0000
11.000 1.4177 0.05612 0.04777 -0.0558 0.2388 1.0000
11.250 1.4404 0.05746 0.04905 -0.0548 0.2267 1.0000
11.500 1.4037 0.06294 0.05493 -0.0520 0.2243 1.0000
11.750 1.3531 0.07002 0.06226 -0.0504 0.2246 1.0000
12.000 1.2847 0.08152 0.07387 -0.0530 0.2270 1.0000
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Polar data table (+)
Polar graphs
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