S5020 (s5020-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 500,000 Max Cl/Cd: 82.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5020-il-500000-n5.txt Download as CSV file: xf-s5020-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5329 0.08894 0.08659 0.0205 0.8080 0.0085
-7.750 -0.5347 0.08533 0.08295 0.0188 0.7906 0.0083
-7.500 -0.5394 0.08180 0.07937 0.0168 0.7750 0.0081
-7.250 -0.5393 0.07706 0.07459 0.0128 0.7621 0.0081
-7.000 -0.5348 0.07222 0.06968 0.0088 0.7508 0.0080
-6.750 -0.5275 0.06707 0.06443 0.0050 0.7407 0.0080
-6.250 -0.5052 0.05541 0.05247 -0.0017 0.7227 0.0082
-6.000 -0.4902 0.04902 0.04583 -0.0039 0.7150 0.0085
-5.750 -0.4729 0.04253 0.03903 -0.0051 0.7072 0.0088
-5.500 -0.4551 0.03639 0.03250 -0.0055 0.7000 0.0096
-5.250 -0.4333 0.03501 0.03099 -0.0057 0.6910 0.0100
-5.000 -0.4110 0.03258 0.02834 -0.0057 0.6829 0.0104
-4.750 -0.3888 0.02840 0.02375 -0.0051 0.6755 0.0106
-4.500 -0.3653 0.02509 0.02006 -0.0044 0.6681 0.0110
-4.250 -0.3409 0.02224 0.01681 -0.0036 0.6605 0.0114
-4.000 -0.3155 0.01985 0.01404 -0.0029 0.6530 0.0118
-3.750 -0.2893 0.01824 0.01211 -0.0024 0.6453 0.0124
-3.500 -0.2625 0.01699 0.01061 -0.0019 0.6373 0.0129
-3.250 -0.2357 0.01568 0.00904 -0.0014 0.6297 0.0131
-3.000 -0.2086 0.01462 0.00777 -0.0010 0.6216 0.0132
-2.750 -0.1813 0.01380 0.00677 -0.0006 0.6139 0.0135
-2.500 -0.1538 0.01322 0.00605 -0.0003 0.6056 0.0138
-2.250 -0.1269 0.01240 0.00511 0.0000 0.5977 0.0141
-2.000 -0.1005 0.01154 0.00416 0.0005 0.5897 0.0148
-1.750 -0.0735 0.01104 0.00359 0.0008 0.5813 0.0152
-1.500 -0.0462 0.01069 0.00319 0.0010 0.5732 0.0160
-1.250 -0.0187 0.01041 0.00287 0.0012 0.5645 0.0170
-1.000 0.0088 0.01013 0.00253 0.0014 0.5561 0.0174
-0.750 0.0364 0.00989 0.00221 0.0016 0.5473 0.0177
-0.500 0.0643 0.00969 0.00195 0.0018 0.5384 0.0183
-0.250 0.0921 0.00955 0.00174 0.0019 0.5296 0.0191
0.000 0.1201 0.00945 0.00157 0.0020 0.5202 0.0202
0.250 0.1482 0.00936 0.00142 0.0022 0.5108 0.0229
0.500 0.1761 0.00926 0.00134 0.0023 0.5014 0.0345
0.750 0.1972 0.00769 0.00127 0.0028 0.4923 0.5285
1.250 0.2974 0.00655 0.00130 -0.0063 0.4676 1.0000
1.500 0.3241 0.00663 0.00129 -0.0060 0.4572 1.0000
1.750 0.3508 0.00672 0.00130 -0.0057 0.4460 1.0000
2.000 0.3775 0.00681 0.00132 -0.0054 0.4344 1.0000
2.250 0.4043 0.00691 0.00135 -0.0051 0.4225 1.0000
2.500 0.4311 0.00702 0.00139 -0.0048 0.4099 1.0000
2.750 0.4578 0.00713 0.00144 -0.0046 0.3977 1.0000
3.000 0.4846 0.00726 0.00151 -0.0044 0.3850 1.0000
3.250 0.5113 0.00740 0.00159 -0.0041 0.3716 1.0000
3.500 0.5381 0.00755 0.00169 -0.0039 0.3584 1.0000
3.750 0.5648 0.00771 0.00179 -0.0037 0.3442 1.0000
4.000 0.5915 0.00788 0.00191 -0.0035 0.3298 1.0000
4.250 0.6181 0.00807 0.00204 -0.0033 0.3147 1.0000
4.500 0.6446 0.00828 0.00220 -0.0032 0.2989 1.0000
4.750 0.6711 0.00849 0.00237 -0.0030 0.2839 1.0000
5.000 0.6976 0.00872 0.00255 -0.0028 0.2693 1.0000
5.250 0.7239 0.00896 0.00274 -0.0026 0.2541 1.0000
5.500 0.7503 0.00921 0.00297 -0.0025 0.2405 1.0000
5.750 0.7765 0.00948 0.00319 -0.0023 0.2257 1.0000
6.000 0.8026 0.00976 0.00344 -0.0022 0.2119 1.0000
6.250 0.8287 0.01004 0.00369 -0.0020 0.1985 1.0000
6.500 0.8546 0.01036 0.00399 -0.0019 0.1843 1.0000
6.750 0.8805 0.01068 0.00429 -0.0017 0.1713 1.0000
7.000 0.9061 0.01103 0.00461 -0.0016 0.1575 1.0000
7.250 0.9317 0.01139 0.00495 -0.0014 0.1450 1.0000
7.500 0.9568 0.01184 0.00534 -0.0013 0.1289 1.0000
7.750 0.9816 0.01231 0.00577 -0.0011 0.1118 1.0000
8.000 1.0059 0.01286 0.00624 -0.0010 0.0927 1.0000
8.250 1.0301 0.01339 0.00672 -0.0008 0.0791 1.0000
8.500 1.0546 0.01387 0.00719 -0.0006 0.0695 1.0000
8.750 1.0785 0.01440 0.00771 -0.0004 0.0595 1.0000
9.000 1.1013 0.01508 0.00835 -0.0001 0.0461 1.0000
9.250 1.1231 0.01589 0.00908 0.0002 0.0324 1.0000
9.500 1.1442 0.01673 0.00988 0.0005 0.0204 1.0000
9.750 1.1624 0.01794 0.01101 0.0011 0.0076 1.0000
10.000 1.1823 0.01884 0.01196 0.0016 0.0056 1.0000
10.250 1.2026 0.01960 0.01282 0.0021 0.0050 1.0000
10.500 1.2218 0.02043 0.01376 0.0027 0.0046 1.0000
10.750 1.2397 0.02133 0.01479 0.0034 0.0043 1.0000
11.000 1.2556 0.02237 0.01595 0.0041 0.0040 1.0000
11.250 1.2697 0.02346 0.01716 0.0050 0.0038 1.0000
11.500 1.2792 0.02486 0.01869 0.0061 0.0036 1.0000
11.750 1.2828 0.02630 0.02025 0.0077 0.0035 1.0000
12.000 1.2780 0.02857 0.02267 0.0089 0.0033 1.0000
12.250 1.2814 0.03050 0.02471 0.0092 0.0032 1.0000
12.500 1.2806 0.03306 0.02740 0.0091 0.0032 1.0000
12.750 1.2868 0.03500 0.02943 0.0090 0.0030 1.0000
13.000 1.2836 0.03813 0.03270 0.0083 0.0030 1.0000
13.250 1.2830 0.04108 0.03577 0.0076 0.0029 1.0000
13.500 1.2793 0.04452 0.03934 0.0066 0.0029 1.0000
13.750 1.2722 0.04853 0.04350 0.0052 0.0028 1.0000
14.000 1.2655 0.05263 0.04773 0.0036 0.0029 1.0000
14.250 1.2564 0.05720 0.05242 0.0018 0.0028 1.0000
14.500 1.2458 0.06215 0.05751 -0.0004 0.0028 1.0000
14.750 1.2362 0.06712 0.06260 -0.0026 0.0028 1.0000
15.000 1.2239 0.07276 0.06837 -0.0052 0.0028 1.0000
15.250 1.2128 0.07844 0.07417 -0.0080 0.0028 1.0000
15.500 1.2011 0.08441 0.08026 -0.0109 0.0027 1.0000
15.750 1.1887 0.09067 0.08664 -0.0140 0.0027 1.0000
16.000 1.1782 0.09670 0.09279 -0.0169 0.0027 1.0000
16.250 1.1635 0.10370 0.09990 -0.0205 0.0027 1.0000
16.500 1.1523 0.11021 0.10652 -0.0238 0.0026 1.0000
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Polar data table (+)
Polar graphs
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