S5020 (s5020-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 50,000 Max Cl/Cd: 33.76 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5020-il-50000-n5.txt Download as CSV file: xf-s5020-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S5020
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5169 0.09545 0.08980 0.0028 1.0000 0.1229
-7.250 -0.4935 0.09037 0.08477 0.0085 1.0000 0.1309
-7.000 -0.4999 0.08711 0.08157 -0.0003 1.0000 0.1380
-6.750 -0.4812 0.08276 0.07724 0.0027 1.0000 0.1437
-6.250 -0.4630 0.07511 0.06966 -0.0027 1.0000 0.1599
-5.750 -0.4188 0.06038 0.05423 -0.0174 1.0000 0.0638
-5.500 -0.4013 0.05607 0.04980 -0.0191 1.0000 0.0596
-5.250 -0.3778 0.05138 0.04430 -0.0219 1.0000 0.0522
-5.000 -0.3587 0.04759 0.04047 -0.0227 1.0000 0.0512
-4.750 -0.3395 0.04428 0.03696 -0.0233 1.0000 0.0503
-4.500 -0.3201 0.04142 0.03374 -0.0237 0.9924 0.0508
-4.250 -0.2831 0.03842 0.03004 -0.0264 0.9597 0.0521
-4.000 -0.2467 0.03560 0.02664 -0.0286 0.9394 0.0525
-3.750 -0.2137 0.03294 0.02354 -0.0299 0.9210 0.0522
-3.500 -0.1824 0.03082 0.02094 -0.0303 0.9040 0.0522
-3.250 -0.1530 0.02909 0.01878 -0.0301 0.8880 0.0525
-3.000 -0.1254 0.02736 0.01680 -0.0297 0.8729 0.0532
-2.750 -0.0984 0.02597 0.01520 -0.0290 0.8585 0.0545
-2.500 -0.0719 0.02491 0.01400 -0.0282 0.8444 0.0579
-2.250 -0.0448 0.02412 0.01296 -0.0274 0.8308 0.0633
-2.000 -0.0171 0.02333 0.01192 -0.0267 0.8177 0.0674
-1.750 0.0081 0.02256 0.01105 -0.0258 0.8049 0.0720
-1.500 0.0331 0.02200 0.01028 -0.0247 0.7924 0.0791
-1.250 0.0580 0.02140 0.00959 -0.0238 0.7804 0.0941
-1.000 0.1290 0.01740 0.00855 -0.0306 0.7706 1.0000
-0.750 0.1519 0.01758 0.00832 -0.0294 0.7587 1.0000
-0.500 0.1755 0.01777 0.00818 -0.0284 0.7463 1.0000
-0.250 0.1992 0.01798 0.00809 -0.0275 0.7340 1.0000
0.000 0.2230 0.01819 0.00806 -0.0266 0.7219 1.0000
0.250 0.2468 0.01841 0.00806 -0.0256 0.7102 1.0000
0.500 0.2704 0.01863 0.00808 -0.0246 0.6989 1.0000
0.750 0.2938 0.01883 0.00808 -0.0235 0.6881 1.0000
1.000 0.3182 0.01908 0.00819 -0.0228 0.6758 1.0000
1.250 0.3426 0.01933 0.00833 -0.0220 0.6637 1.0000
1.500 0.3668 0.01958 0.00847 -0.0212 0.6518 1.0000
1.750 0.3910 0.01983 0.00861 -0.0204 0.6402 1.0000
2.000 0.4150 0.02005 0.00874 -0.0194 0.6288 1.0000
2.250 0.4392 0.02028 0.00888 -0.0184 0.6174 1.0000
2.500 0.4638 0.02055 0.00913 -0.0178 0.6047 1.0000
2.750 0.4884 0.02083 0.00937 -0.0171 0.5920 1.0000
3.000 0.5129 0.02110 0.00962 -0.0163 0.5792 1.0000
3.250 0.5373 0.02136 0.00987 -0.0155 0.5664 1.0000
3.500 0.5618 0.02162 0.01015 -0.0147 0.5535 1.0000
3.750 0.5862 0.02188 0.01041 -0.0139 0.5405 1.0000
4.000 0.6106 0.02214 0.01068 -0.0131 0.5271 1.0000
4.250 0.6351 0.02241 0.01097 -0.0123 0.5134 1.0000
4.500 0.6594 0.02269 0.01132 -0.0115 0.4993 1.0000
4.750 0.6838 0.02298 0.01165 -0.0108 0.4847 1.0000
5.000 0.7080 0.02328 0.01201 -0.0100 0.4697 1.0000
5.250 0.7322 0.02360 0.01239 -0.0093 0.4543 1.0000
5.500 0.7562 0.02393 0.01283 -0.0085 0.4386 1.0000
5.750 0.7801 0.02427 0.01323 -0.0077 0.4228 1.0000
6.000 0.8039 0.02462 0.01363 -0.0069 0.4068 1.0000
6.250 0.8274 0.02501 0.01407 -0.0061 0.3906 1.0000
6.500 0.8505 0.02556 0.01475 -0.0055 0.3725 1.0000
6.750 0.8733 0.02609 0.01543 -0.0048 0.3548 1.0000
7.000 0.8958 0.02663 0.01603 -0.0040 0.3377 1.0000
7.250 0.9180 0.02719 0.01663 -0.0032 0.3206 1.0000
7.500 0.9393 0.02799 0.01758 -0.0026 0.3024 1.0000
7.750 0.9600 0.02878 0.01848 -0.0019 0.2846 1.0000
8.000 0.9804 0.02962 0.01946 -0.0012 0.2680 1.0000
8.250 1.0001 0.03051 0.02040 -0.0004 0.2517 1.0000
8.500 1.0187 0.03158 0.02160 0.0003 0.2357 1.0000
8.750 1.0361 0.03276 0.02293 0.0011 0.2197 1.0000
9.000 1.0528 0.03401 0.02431 0.0018 0.2050 1.0000
9.250 1.0682 0.03535 0.02578 0.0026 0.1908 1.0000
9.500 1.0826 0.03678 0.02734 0.0034 0.1779 1.0000
9.750 1.0960 0.03829 0.02903 0.0043 0.1658 1.0000
10.000 1.1079 0.03981 0.03062 0.0052 0.1545 1.0000
10.250 1.1174 0.04174 0.03279 0.0060 0.1442 1.0000
10.500 1.1245 0.04382 0.03509 0.0068 0.1348 1.0000
10.750 1.1303 0.04571 0.03705 0.0077 0.1260 1.0000
11.000 1.1310 0.04805 0.03961 0.0086 0.1186 1.0000
11.250 1.1321 0.05053 0.04222 0.0094 0.1123 1.0000
11.500 1.1275 0.05351 0.04541 0.0095 0.1061 1.0000
11.750 1.1253 0.05630 0.04825 0.0094 0.1002 1.0000
12.000 1.1144 0.06053 0.05277 0.0083 0.0956 1.0000
12.250 1.1176 0.06288 0.05503 0.0084 0.0892 1.0000
12.500 1.0999 0.06859 0.06109 0.0060 0.0868 1.0000
12.750 1.0816 0.07479 0.06753 0.0031 0.0848 1.0000
13.000 1.0607 0.08191 0.07485 -0.0006 0.0836 1.0000
13.250 1.0649 0.08393 0.07676 -0.0009 0.0762 1.0000
13.500 1.0424 0.09200 0.08503 -0.0053 0.0761 1.0000
13.750 1.0162 0.10146 0.09462 -0.0106 0.0765 1.0000
14.000 0.9891 0.11195 0.10516 -0.0165 0.0771 1.0000
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Polar data table (+)
Polar graphs
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