NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 50,000 Max Cl/Cd: 20.66 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20404-il-50000.txt Download as CSV file: xf-sc20404-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6876 0.11145 0.10485 0.0212 1.0000 0.2009
-8.250 -0.6819 0.10731 0.10075 0.0214 1.0000 0.2138
-8.000 -0.6795 0.10359 0.09710 0.0210 1.0000 0.2271
-7.750 -0.6632 0.09846 0.09197 0.0237 1.0000 0.2452
-7.500 -0.6606 0.09511 0.08867 0.0238 1.0000 0.2638
-7.250 -0.6577 0.09145 0.08509 0.0238 1.0000 0.2837
-7.000 -0.6546 0.08808 0.08178 0.0238 1.0000 0.3088
-6.750 -0.6415 0.08434 0.07805 0.0276 1.0000 0.3404
-6.250 -0.6222 0.07771 0.07136 0.0344 1.0000 0.4197
-6.000 -0.6114 0.07499 0.06868 0.0405 1.0000 0.4813
-5.750 -0.5732 0.07081 0.06441 0.0485 1.0000 0.5766
-5.250 -0.5047 0.04526 0.03699 -0.0307 1.0000 0.1590
-5.000 -0.4636 0.03980 0.03043 -0.0342 1.0000 0.1206
-4.750 -0.4338 0.03590 0.02609 -0.0352 1.0000 0.1190
-4.500 -0.4024 0.03229 0.02195 -0.0358 1.0000 0.1150
-4.250 -0.3681 0.02941 0.01817 -0.0358 1.0000 0.1077
-4.000 -0.3381 0.02662 0.01498 -0.0353 1.0000 0.1072
-3.750 -0.3100 0.02416 0.01228 -0.0342 1.0000 0.1103
-3.500 -0.2842 0.02218 0.01022 -0.0324 1.0000 0.1192
-3.250 -0.2600 0.02033 0.00850 -0.0312 1.0000 0.1523
-3.000 -0.2316 0.01726 0.00625 -0.0312 1.0000 0.2556
-2.750 -0.2237 0.01440 0.00583 -0.0170 1.0000 1.0000
-2.500 -0.2037 0.01413 0.00490 -0.0163 1.0000 1.0000
-2.250 -0.1813 0.01392 0.00429 -0.0161 1.0000 1.0000
-2.000 -0.1566 0.01376 0.00378 -0.0162 1.0000 1.0000
-1.750 -0.1305 0.01364 0.00336 -0.0165 1.0000 1.0000
-1.500 -0.1037 0.01355 0.00302 -0.0169 1.0000 1.0000
-1.250 -0.0766 0.01349 0.00276 -0.0172 1.0000 1.0000
-1.000 -0.0493 0.01345 0.00257 -0.0175 1.0000 1.0000
-0.750 -0.0220 0.01343 0.00240 -0.0178 1.0000 1.0000
-0.500 0.0052 0.01343 0.00231 -0.0181 1.0000 1.0000
-0.250 0.0323 0.01344 0.00228 -0.0183 1.0000 1.0000
0.000 0.0593 0.01347 0.00231 -0.0184 1.0000 1.0000
0.250 0.0862 0.01352 0.00240 -0.0185 1.0000 1.0000
0.500 0.1130 0.01357 0.00254 -0.0186 1.0000 1.0000
0.750 0.1397 0.01365 0.00279 -0.0186 1.0000 1.0000
1.000 0.1663 0.01374 0.00304 -0.0186 1.0000 1.0000
1.250 0.1928 0.01384 0.00336 -0.0186 1.0000 1.0000
1.500 0.2193 0.01396 0.00375 -0.0186 1.0000 1.0000
1.750 0.2457 0.01411 0.00423 -0.0185 1.0000 1.0000
2.000 0.2721 0.01427 0.00483 -0.0183 1.0000 1.0000
2.250 0.2987 0.01446 0.00561 -0.0181 1.0000 1.0000
2.500 0.3743 0.02093 0.00914 -0.0226 0.1456 1.0000
2.750 0.4056 0.02286 0.01114 -0.0223 0.1142 1.0000
3.000 0.4365 0.02535 0.01367 -0.0218 0.1057 1.0000
3.250 0.4681 0.02784 0.01662 -0.0211 0.1043 1.0000
3.500 0.4987 0.03094 0.02009 -0.0206 0.1057 1.0000
3.750 0.5314 0.03393 0.02402 -0.0198 0.1147 1.0000
4.000 0.5631 0.03776 0.02856 -0.0195 0.1294 1.0000
4.250 0.5930 0.04227 0.03353 -0.0196 0.1456 1.0000
4.500 0.6418 0.05972 0.05418 -0.0994 0.7421 1.0000
4.750 0.6231 0.06229 0.05663 -0.0998 0.7733 1.0000
5.750 0.7627 0.07814 0.07261 -0.0631 0.3737 1.0000
6.000 0.7738 0.08217 0.07672 -0.0573 0.3323 1.0000
6.250 0.7729 0.08569 0.08020 -0.0585 0.2993 1.0000
6.500 0.7785 0.08974 0.08421 -0.0577 0.2729 1.0000
6.750 0.7897 0.09441 0.08883 -0.0549 0.2510 1.0000
7.000 0.7870 0.09818 0.09257 -0.0585 0.2340 1.0000
7.250 0.7887 0.10232 0.09666 -0.0599 0.2190 1.0000
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Polar data table (+)
Polar graphs
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