S5020 (s5020-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 500,000 Max Cl/Cd: 87.98 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5020-il-500000.txt Download as CSV file: xf-s5020-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5231 0.09106 0.08918 0.0206 1.0000 0.0139
-7.750 -0.5211 0.08742 0.08558 0.0184 1.0000 0.0141
-7.500 -0.5211 0.08373 0.08194 0.0158 1.0000 0.0143
-7.250 -0.5167 0.07949 0.07761 0.0112 0.9058 0.0146
-7.000 -0.5158 0.07579 0.07375 0.0088 0.8671 0.0147
-6.750 -0.5106 0.07161 0.06945 0.0058 0.8443 0.0150
-6.500 -0.5018 0.06702 0.06475 0.0025 0.8266 0.0156
-6.250 -0.4880 0.06190 0.05946 -0.0011 0.8118 0.0165
-6.000 -0.4660 0.05703 0.05434 -0.0041 0.7991 0.0172
-5.750 -0.4484 0.05258 0.04965 -0.0053 0.7874 0.0173
-5.500 -0.4394 0.04466 0.04141 -0.0068 0.7775 0.0178
-5.250 -0.4237 0.04161 0.03824 -0.0073 0.7669 0.0184
-5.000 -0.4042 0.03926 0.03574 -0.0074 0.7568 0.0191
-4.750 -0.3828 0.03668 0.03297 -0.0075 0.7466 0.0201
-4.500 -0.3588 0.03398 0.03000 -0.0073 0.7373 0.0223
-4.250 -0.3280 0.03337 0.02893 -0.0061 0.7284 0.0244
-4.000 -0.3117 0.02705 0.02227 -0.0062 0.7202 0.0260
-3.750 -0.2878 0.02547 0.02057 -0.0060 0.7113 0.0273
-3.500 -0.2624 0.02396 0.01885 -0.0057 0.7026 0.0297
-3.250 -0.2348 0.02251 0.01687 -0.0046 0.6940 0.0348
-3.000 -0.2106 0.02032 0.01460 -0.0046 0.6860 0.0373
-2.750 -0.1838 0.01934 0.01349 -0.0043 0.6769 0.0410
-2.000 -0.0979 0.01340 0.00649 -0.0012 0.6533 0.0251
-1.750 -0.0704 0.01261 0.00559 -0.0008 0.6449 0.0248
-1.500 -0.0434 0.01167 0.00458 -0.0003 0.6364 0.0250
-1.250 -0.0169 0.01091 0.00373 0.0002 0.6285 0.0254
-1.000 0.0100 0.01033 0.00312 0.0005 0.6196 0.0271
-0.750 0.0374 0.00998 0.00270 0.0009 0.6113 0.0281
-0.500 0.0650 0.00969 0.00235 0.0011 0.6025 0.0293
-0.250 0.0929 0.00947 0.00207 0.0013 0.5936 0.0316
0.000 0.1207 0.00930 0.00182 0.0016 0.5852 0.0372
0.250 0.1450 0.00817 0.00163 0.0019 0.5761 0.3406
0.500 0.2178 0.00629 0.00163 -0.0075 0.5642 1.0000
0.750 0.2442 0.00634 0.00157 -0.0071 0.5552 1.0000
1.000 0.2708 0.00639 0.00153 -0.0067 0.5453 1.0000
1.250 0.2974 0.00644 0.00150 -0.0064 0.5356 1.0000
1.500 0.3240 0.00651 0.00149 -0.0060 0.5259 1.0000
1.750 0.3507 0.00658 0.00148 -0.0057 0.5156 1.0000
2.000 0.3775 0.00664 0.00150 -0.0054 0.5050 1.0000
2.250 0.4042 0.00672 0.00152 -0.0051 0.4942 1.0000
2.500 0.4310 0.00682 0.00155 -0.0048 0.4834 1.0000
2.750 0.4577 0.00692 0.00159 -0.0045 0.4720 1.0000
3.000 0.4846 0.00701 0.00164 -0.0042 0.4601 1.0000
3.250 0.5114 0.00711 0.00170 -0.0040 0.4481 1.0000
3.500 0.5382 0.00723 0.00179 -0.0037 0.4356 1.0000
3.750 0.5650 0.00735 0.00187 -0.0035 0.4227 1.0000
4.000 0.5918 0.00749 0.00197 -0.0033 0.4090 1.0000
4.250 0.6186 0.00765 0.00208 -0.0031 0.3947 1.0000
4.500 0.6453 0.00781 0.00222 -0.0029 0.3796 1.0000
4.750 0.6719 0.00799 0.00236 -0.0027 0.3640 1.0000
5.000 0.6985 0.00819 0.00251 -0.0025 0.3482 1.0000
5.250 0.7250 0.00841 0.00268 -0.0024 0.3322 1.0000
5.500 0.7515 0.00865 0.00289 -0.0022 0.3154 1.0000
5.750 0.7779 0.00889 0.00310 -0.0020 0.2993 1.0000
6.000 0.8043 0.00915 0.00333 -0.0019 0.2820 1.0000
6.250 0.8305 0.00944 0.00358 -0.0018 0.2651 1.0000
6.500 0.8566 0.00976 0.00386 -0.0016 0.2480 1.0000
6.750 0.8825 0.01010 0.00416 -0.0015 0.2314 1.0000
7.000 0.9085 0.01043 0.00447 -0.0014 0.2154 1.0000
7.250 0.9343 0.01079 0.00480 -0.0013 0.1988 1.0000
7.500 0.9598 0.01118 0.00518 -0.0012 0.1828 1.0000
7.750 0.9852 0.01160 0.00556 -0.0010 0.1672 1.0000
8.000 1.0101 0.01209 0.00599 -0.0009 0.1499 1.0000
8.250 1.0350 0.01255 0.00641 -0.0008 0.1328 1.0000
8.500 1.0596 0.01305 0.00689 -0.0006 0.1173 1.0000
8.750 1.0838 0.01357 0.00739 -0.0005 0.1033 1.0000
9.000 1.1078 0.01413 0.00792 -0.0003 0.0904 1.0000
9.250 1.1313 0.01472 0.00849 -0.0001 0.0780 1.0000
9.500 1.1540 0.01541 0.00912 0.0001 0.0638 1.0000
9.750 1.1762 0.01612 0.00981 0.0004 0.0514 1.0000
10.000 1.1970 0.01701 0.01063 0.0008 0.0363 1.0000
10.250 1.2121 0.01864 0.01208 0.0015 0.0148 1.0000
10.500 1.2283 0.02000 0.01349 0.0022 0.0105 1.0000
10.750 1.2459 0.02103 0.01465 0.0029 0.0094 1.0000
11.000 1.2615 0.02217 0.01591 0.0037 0.0087 1.0000
11.250 1.2734 0.02354 0.01740 0.0047 0.0081 1.0000
11.500 1.2795 0.02524 0.01923 0.0060 0.0077 1.0000
11.750 1.2754 0.02722 0.02135 0.0078 0.0075 1.0000
12.000 1.2716 0.02961 0.02389 0.0085 0.0074 1.0000
12.250 1.2652 0.03267 0.02709 0.0086 0.0072 1.0000
12.500 1.2675 0.03504 0.02958 0.0084 0.0070 1.0000
12.750 1.2641 0.03817 0.03284 0.0079 0.0070 1.0000
13.000 1.2633 0.04114 0.03592 0.0073 0.0068 1.0000
13.250 1.2617 0.04431 0.03920 0.0064 0.0066 1.0000
13.500 1.2548 0.04820 0.04323 0.0053 0.0066 1.0000
13.750 1.2496 0.05200 0.04714 0.0040 0.0065 1.0000
14.000 1.2432 0.05607 0.05133 0.0026 0.0064 1.0000
14.250 1.2353 0.06044 0.05583 0.0010 0.0063 1.0000
14.500 1.2271 0.06499 0.06049 -0.0008 0.0062 1.0000
14.750 1.2189 0.06974 0.06537 -0.0028 0.0062 1.0000
15.000 1.2105 0.07466 0.07041 -0.0049 0.0063 1.0000
15.250 1.2038 0.07956 0.07541 -0.0072 0.0062 1.0000
15.500 1.1943 0.08493 0.08092 -0.0095 0.0062 1.0000
15.750 1.1860 0.09037 0.08647 -0.0121 0.0061 1.0000
16.000 1.1772 0.09597 0.09218 -0.0148 0.0061 1.0000
16.250 1.1679 0.10181 0.09815 -0.0177 0.0061 1.0000
16.500 1.1581 0.10790 0.10436 -0.0207 0.0061 1.0000
16.750 1.1478 0.11426 0.11085 -0.0239 0.0061 1.0000
17.000 1.1380 0.12072 0.11743 -0.0273 0.0062 1.0000
17.250 1.1293 0.12710 0.12392 -0.0308 0.0060 1.0000
17.500 1.1175 0.13432 0.13128 -0.0348 0.0061 1.0000
17.750 1.1063 0.14161 0.13869 -0.0389 0.0062 1.0000
18.000 1.0955 0.14909 0.14628 -0.0431 0.0061 1.0000
18.250 1.0832 0.15714 0.15446 -0.0478 0.0063 1.0000
18.500 1.0697 0.16587 0.16332 -0.0529 0.0063 1.0000
18.750 1.0543 0.17552 0.17309 -0.0585 0.0064 1.0000
19.000 1.0353 0.18695 0.18463 -0.0650 0.0066 1.0000
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Polar data table (+)
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