S5020 (s5020-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 100,000 Max Cl/Cd: 45.97 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5020-il-100000.txt Download as CSV file: xf-s5020-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4359 0.11429 0.11028 0.0229 1.0000 0.0673
-9.250 -0.4354 0.11070 0.10672 0.0207 1.0000 0.0700
-9.000 -0.5242 0.11255 0.10821 0.0256 1.0000 0.0636
-8.750 -0.5180 0.10903 0.10472 0.0241 1.0000 0.0661
-8.500 -0.5152 0.10566 0.10140 0.0215 1.0000 0.0695
-8.250 -0.5178 0.10278 0.09860 0.0170 1.0000 0.0715
-8.000 -0.5258 0.10020 0.09612 0.0105 1.0000 0.0723
-7.750 -0.5286 0.09691 0.09285 0.0024 1.0000 0.0727
-7.500 -0.5094 0.09055 0.08657 0.0098 1.0000 0.0756
-7.250 -0.4993 0.08693 0.08298 0.0094 1.0000 0.0786
-7.000 -0.4925 0.08308 0.07917 0.0058 1.0000 0.0819
-6.750 -0.4872 0.07913 0.07514 -0.0046 1.0000 0.0862
-6.500 -0.4782 0.07382 0.06981 -0.0084 1.0000 0.0883
-6.250 -0.4627 0.07013 0.06624 -0.0062 1.0000 0.0921
-6.000 -0.4474 0.06790 0.06347 -0.0162 1.0000 0.1013
-5.750 -0.3819 0.04939 0.04585 -0.0165 1.0000 0.1104
-5.500 -0.3703 0.04427 0.04059 -0.0216 1.0000 0.1182
-5.250 -0.3600 0.04143 0.03779 -0.0218 0.9970 0.1253
-5.000 -0.3274 0.03536 0.03144 -0.0290 0.9739 0.1464
-4.750 -0.2967 0.03113 0.02724 -0.0314 0.9578 0.1666
-4.500 -0.2728 0.02728 0.02327 -0.0334 0.9392 0.1923
-4.250 -0.2922 0.04155 0.03705 -0.0306 0.9598 0.2063
-4.000 -0.2424 0.02243 0.01833 -0.0310 0.9034 0.2507
-3.250 -0.1526 0.02775 0.02029 -0.0337 0.8951 0.0886
-3.000 -0.1283 0.02582 0.01812 -0.0322 0.8805 0.0822
-2.750 -0.1042 0.02430 0.01626 -0.0306 0.8668 0.0803
-2.500 -0.0787 0.02290 0.01436 -0.0287 0.8540 0.0757
-2.250 -0.0534 0.02216 0.01328 -0.0270 0.8417 0.0734
-2.000 -0.0287 0.02113 0.01208 -0.0254 0.8298 0.0732
-1.750 -0.0034 0.01989 0.01080 -0.0243 0.8174 0.0742
-1.500 0.0207 0.01893 0.00990 -0.0232 0.8055 0.0773
-1.250 0.0445 0.01839 0.00934 -0.0219 0.7939 0.0856
-1.000 0.0670 0.01771 0.00866 -0.0203 0.7831 0.0954
-0.750 0.1446 0.01368 0.00731 -0.0279 0.7732 1.0000
-0.500 0.1683 0.01386 0.00719 -0.0269 0.7608 1.0000
-0.250 0.1919 0.01404 0.00712 -0.0259 0.7488 1.0000
0.000 0.2154 0.01423 0.00710 -0.0248 0.7373 1.0000
0.250 0.2385 0.01440 0.00708 -0.0235 0.7264 1.0000
0.500 0.2615 0.01456 0.00705 -0.0222 0.7157 1.0000
0.750 0.2861 0.01475 0.00711 -0.0214 0.7034 1.0000
1.000 0.3106 0.01495 0.00719 -0.0206 0.6915 1.0000
1.250 0.3348 0.01514 0.00726 -0.0196 0.6799 1.0000
1.500 0.3586 0.01530 0.00730 -0.0185 0.6691 1.0000
1.750 0.3825 0.01544 0.00732 -0.0173 0.6582 1.0000
2.000 0.4075 0.01564 0.00745 -0.0166 0.6456 1.0000
2.250 0.4324 0.01583 0.00758 -0.0158 0.6331 1.0000
2.500 0.4573 0.01601 0.00771 -0.0150 0.6209 1.0000
2.750 0.4821 0.01617 0.00781 -0.0141 0.6088 1.0000
3.000 0.5068 0.01630 0.00787 -0.0131 0.5969 1.0000
3.250 0.5315 0.01640 0.00788 -0.0120 0.5853 1.0000
3.500 0.5567 0.01654 0.00801 -0.0113 0.5721 1.0000
3.750 0.5819 0.01669 0.00814 -0.0105 0.5584 1.0000
4.000 0.6072 0.01684 0.00826 -0.0097 0.5444 1.0000
4.250 0.6326 0.01698 0.00838 -0.0090 0.5303 1.0000
4.500 0.6579 0.01712 0.00852 -0.0082 0.5158 1.0000
4.750 0.6833 0.01727 0.00865 -0.0075 0.5011 1.0000
5.000 0.7086 0.01742 0.00876 -0.0067 0.4860 1.0000
5.250 0.7341 0.01765 0.00904 -0.0061 0.4689 1.0000
5.500 0.7594 0.01787 0.00932 -0.0055 0.4515 1.0000
5.750 0.7847 0.01808 0.00953 -0.0049 0.4342 1.0000
6.000 0.8098 0.01830 0.00971 -0.0042 0.4169 1.0000
6.250 0.8349 0.01860 0.01000 -0.0036 0.3986 1.0000
6.500 0.8597 0.01896 0.01045 -0.0031 0.3789 1.0000
6.750 0.8844 0.01931 0.01076 -0.0024 0.3602 1.0000
7.000 0.9087 0.01978 0.01126 -0.0019 0.3405 1.0000
7.250 0.9328 0.02029 0.01180 -0.0014 0.3205 1.0000
7.500 0.9567 0.02085 0.01227 -0.0008 0.3020 1.0000
7.750 0.9799 0.02153 0.01311 -0.0004 0.2814 1.0000
8.000 1.0028 0.02223 0.01378 0.0002 0.2624 1.0000
8.250 1.0253 0.02305 0.01460 0.0007 0.2439 1.0000
8.500 1.0470 0.02393 0.01560 0.0012 0.2249 1.0000
8.750 1.0684 0.02488 0.01658 0.0018 0.2076 1.0000
9.000 1.0894 0.02590 0.01757 0.0024 0.1912 1.0000
9.250 1.1097 0.02712 0.01880 0.0030 0.1759 1.0000
9.500 1.1287 0.02835 0.02018 0.0036 0.1609 1.0000
9.750 1.1475 0.02974 0.02164 0.0043 0.1475 1.0000
10.000 1.1656 0.03121 0.02316 0.0051 0.1348 1.0000
10.250 1.1820 0.03267 0.02471 0.0058 0.1220 1.0000
10.500 1.1932 0.03384 0.02604 0.0067 0.1085 1.0000
10.750 1.1981 0.03485 0.02723 0.0076 0.0945 1.0000
11.000 1.2025 0.03648 0.02894 0.0087 0.0826 1.0000
11.250 1.2027 0.03861 0.03108 0.0100 0.0712 1.0000
11.500 1.1948 0.04083 0.03352 0.0115 0.0629 1.0000
11.750 1.1878 0.04384 0.03666 0.0123 0.0554 1.0000
12.000 1.1857 0.04648 0.03925 0.0127 0.0501 1.0000
12.250 1.1815 0.05019 0.04320 0.0131 0.0460 1.0000
12.500 1.1773 0.05375 0.04699 0.0130 0.0431 1.0000
12.750 1.1752 0.05715 0.05051 0.0127 0.0411 1.0000
13.000 1.1754 0.06079 0.05417 0.0128 0.0391 1.0000
13.250 1.1672 0.06587 0.05943 0.0121 0.0382 1.0000
13.500 1.1529 0.07090 0.06474 0.0101 0.0380 1.0000
13.750 1.1378 0.07637 0.07045 0.0076 0.0379 1.0000
14.000 1.1201 0.08249 0.07679 0.0045 0.0379 1.0000
14.250 1.1012 0.08917 0.08367 0.0007 0.0380 1.0000
14.500 1.0810 0.09645 0.09113 -0.0035 0.0382 1.0000
14.750 1.0599 0.10435 0.09922 -0.0086 0.0385 1.0000
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Polar data table (+)
Polar graphs
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