NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 1,000,000 Max Cl/Cd: 55.15 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20404-il-1000000-n5.txt Download as CSV file: xf-sc20404-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0404 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6594 0.09545 0.09387 0.0179 1.0000 0.0038
-8.250 -0.6570 0.09113 0.08957 0.0154 1.0000 0.0038
-8.000 -0.6550 0.08671 0.08516 0.0124 1.0000 0.0038
-7.750 -0.6497 0.08163 0.08010 0.0072 1.0000 0.0038
-7.500 -0.6387 0.07513 0.07359 -0.0019 1.0000 0.0038
-7.250 -0.6296 0.06724 0.06564 -0.0109 1.0000 0.0036
-7.000 -0.6167 0.05997 0.05827 -0.0178 1.0000 0.0033
-6.750 -0.5998 0.05339 0.05154 -0.0229 1.0000 0.0032
-6.500 -0.5801 0.04714 0.04511 -0.0268 1.0000 0.0030
-6.250 -0.5577 0.04107 0.03880 -0.0298 1.0000 0.0028
-6.000 -0.5326 0.03504 0.03246 -0.0321 1.0000 0.0026
-5.750 -0.5049 0.02881 0.02584 -0.0338 1.0000 0.0024
-5.500 -0.4734 0.02111 0.01752 -0.0352 1.0000 0.0022
-5.250 -0.4392 0.01332 0.00879 -0.0363 1.0000 0.0020
-5.000 -0.4092 0.01073 0.00579 -0.0368 1.0000 0.0021
-4.750 -0.3796 0.00940 0.00424 -0.0373 1.0000 0.0025
-4.500 -0.3517 0.00916 0.00394 -0.0374 1.0000 0.0036
-4.250 -0.3244 0.00914 0.00394 -0.0375 1.0000 0.0039
-4.000 -0.2944 0.00810 0.00273 -0.0381 1.0000 0.0055
-3.750 -0.2661 0.00778 0.00239 -0.0384 1.0000 0.0071
-3.500 -0.2380 0.00755 0.00214 -0.0385 1.0000 0.0094
-3.250 -0.2106 0.00748 0.00208 -0.0385 1.0000 0.0101
-3.000 -0.1821 0.00714 0.00166 -0.0387 1.0000 0.0110
-2.750 -0.1538 0.00686 0.00124 -0.0389 1.0000 0.0134
-2.500 -0.1259 0.00667 0.00106 -0.0389 1.0000 0.0192
-2.250 -0.0984 0.00650 0.00094 -0.0389 1.0000 0.0334
-2.000 -0.0711 0.00632 0.00086 -0.0389 1.0000 0.0581
-1.750 -0.0438 0.00611 0.00078 -0.0389 1.0000 0.0979
-1.500 -0.0164 0.00584 0.00072 -0.0391 1.0000 0.1610
-1.250 0.0152 0.00463 0.00061 -0.0410 1.0000 0.5046
-1.000 0.0431 0.00430 0.00064 -0.0412 1.0000 0.6156
-0.750 0.0818 0.00410 0.00064 -0.0438 0.9916 0.6751
-0.500 0.1219 0.00407 0.00064 -0.0464 0.9344 0.7068
-0.250 0.1412 0.00465 0.00065 -0.0440 0.7586 0.7218
0.000 0.1646 0.00631 0.00080 -0.0438 0.3158 0.7370
0.250 0.1915 0.00700 0.00091 -0.0441 0.1234 0.7530
0.500 0.2192 0.00724 0.00100 -0.0442 0.0684 0.7665
0.750 0.2470 0.00739 0.00110 -0.0442 0.0412 0.7787
1.000 0.2747 0.00756 0.00122 -0.0442 0.0195 0.7888
1.250 0.3026 0.00771 0.00135 -0.0442 0.0135 0.7977
1.500 0.3305 0.00790 0.00164 -0.0441 0.0117 0.8066
1.750 0.3582 0.00813 0.00203 -0.0440 0.0114 0.8159
2.000 0.3857 0.00859 0.00264 -0.0438 0.0099 0.8254
2.250 0.4130 0.00889 0.00303 -0.0437 0.0092 0.8345
2.500 0.4405 0.00883 0.00296 -0.0437 0.0080 0.8435
2.750 0.4679 0.00886 0.00298 -0.0437 0.0054 0.8541
3.000 0.4944 0.00948 0.00373 -0.0434 0.0037 0.8664
3.250 0.5211 0.00968 0.00399 -0.0431 0.0033 0.8798
3.500 0.5476 0.00993 0.00435 -0.0428 0.0023 0.8932
3.750 0.5728 0.01089 0.00552 -0.0421 0.0019 0.9079
4.000 0.5965 0.01256 0.00754 -0.0407 0.0018 0.9284
4.250 0.6176 0.01680 0.01251 -0.0382 0.0018 0.9770
4.500 0.6412 0.02582 0.02245 -0.0355 0.0021 1.0000
4.750 0.6644 0.03198 0.02908 -0.0341 0.0022 1.0000
5.000 0.6865 0.03767 0.03512 -0.0334 0.0024 1.0000
5.250 0.7075 0.04326 0.04098 -0.0333 0.0026 1.0000
5.500 0.7269 0.04893 0.04688 -0.0337 0.0027 1.0000
5.750 0.7445 0.05482 0.05296 -0.0349 0.0029 1.0000
6.000 0.7596 0.06109 0.05940 -0.0370 0.0031 1.0000
6.250 0.7675 0.06884 0.06729 -0.0403 0.0035 1.0000
6.500 0.7793 0.07468 0.07321 -0.0435 0.0035 1.0000
6.750 0.7897 0.08040 0.07900 -0.0473 0.0035 1.0000
7.000 0.7983 0.08606 0.08471 -0.0517 0.0035 1.0000
7.250 0.8048 0.09166 0.09033 -0.0567 0.0035 1.0000
7.500 0.8071 0.09694 0.09562 -0.0619 0.0035 1.0000
7.750 0.8060 0.10165 0.10031 -0.0656 0.0035 1.0000
8.000 0.8059 0.10625 0.10490 -0.0684 0.0035 1.0000
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Polar data table (+)
Polar graphs
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