NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 50,000 Max Cl/Cd: 25.9 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20414-il-50000.txt Download as CSV file: xf-sc20414-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0414 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6917 0.08109 0.07275 -0.0423 1.0000 0.1822
-9.750 -0.7065 0.07550 0.06717 -0.0430 1.0000 0.1801
-9.500 -0.7413 0.06961 0.06124 -0.0434 1.0000 0.1770
-9.250 -0.7798 0.06356 0.05499 -0.0437 1.0000 0.1737
-9.000 -0.8009 0.05852 0.04961 -0.0431 1.0000 0.1720
-8.750 -0.8048 0.05456 0.04536 -0.0424 1.0000 0.1724
-8.500 -0.8004 0.05130 0.04184 -0.0416 1.0000 0.1749
-8.250 -0.7935 0.04812 0.03831 -0.0410 1.0000 0.1779
-8.000 -0.7832 0.04500 0.03473 -0.0407 1.0000 0.1809
-7.750 -0.7681 0.04215 0.03154 -0.0403 1.0000 0.1848
-7.500 -0.7490 0.04023 0.02970 -0.0392 1.0000 0.1909
-7.250 -0.7301 0.03807 0.02719 -0.0387 1.0000 0.1974
-7.000 -0.7101 0.03611 0.02517 -0.0378 1.0000 0.2043
-6.750 -0.6894 0.03449 0.02342 -0.0370 1.0000 0.2137
-6.500 -0.6687 0.03294 0.02192 -0.0357 1.0000 0.2232
-6.250 -0.6476 0.03154 0.02047 -0.0344 1.0000 0.2358
-6.000 -0.6269 0.03030 0.01929 -0.0329 1.0000 0.2507
-5.750 -0.6074 0.02920 0.01841 -0.0308 1.0000 0.2691
-5.500 -0.5886 0.02810 0.01757 -0.0287 1.0000 0.2938
-5.250 -0.5706 0.02681 0.01663 -0.0269 1.0000 0.3314
-5.000 -0.5564 0.02532 0.01610 -0.0243 1.0000 0.4006
-4.750 -0.5538 0.02708 0.01916 -0.0138 1.0000 0.5080
-4.500 -0.5425 0.03093 0.02302 -0.0045 1.0000 0.5946
-4.250 -0.5300 0.03420 0.02617 0.0041 1.0000 0.6347
-4.000 -0.5161 0.03651 0.02834 0.0112 1.0000 0.6683
-3.750 -0.5028 0.03797 0.02968 0.0170 1.0000 0.7009
-3.500 -0.4808 0.03942 0.03101 0.0230 1.0000 0.7273
-3.250 -0.4659 0.03986 0.03133 0.0273 1.0000 0.7574
-3.000 -0.4403 0.04022 0.03155 0.0307 1.0000 0.7881
-2.750 -0.4044 0.04017 0.03136 0.0321 1.0000 0.8215
-2.250 -0.2150 0.03811 0.02875 0.0132 1.0000 0.9154
-2.000 -0.1532 0.03661 0.02710 0.0061 1.0000 0.9422
-1.750 -0.1034 0.03533 0.02573 0.0005 1.0000 0.9606
-1.500 -0.0686 0.03443 0.02478 -0.0027 1.0000 0.9727
-1.250 -0.0409 0.03379 0.02411 -0.0047 1.0000 0.9819
-1.000 -0.0062 0.03312 0.02342 -0.0080 1.0000 0.9904
-0.750 0.0235 0.03266 0.02296 -0.0105 1.0000 0.9974
-0.500 0.0365 0.03249 0.02281 -0.0099 1.0000 1.0000
-0.250 0.0387 0.03245 0.02280 -0.0073 1.0000 1.0000
0.000 0.0409 0.03243 0.02281 -0.0047 1.0000 1.0000
0.250 0.0430 0.03242 0.02284 -0.0021 1.0000 1.0000
0.500 0.0452 0.03243 0.02290 0.0004 1.0000 1.0000
0.750 0.0472 0.03246 0.02297 0.0030 1.0000 1.0000
1.000 0.0491 0.03251 0.02306 0.0055 1.0000 1.0000
1.250 0.0509 0.03257 0.02318 0.0080 1.0000 1.0000
1.500 0.0524 0.03264 0.02331 0.0105 1.0000 1.0000
1.750 0.0536 0.03274 0.02347 0.0129 1.0000 1.0000
2.000 0.0544 0.03286 0.02366 0.0154 1.0000 1.0000
2.250 0.0547 0.03300 0.02387 0.0178 1.0000 1.0000
2.500 0.0545 0.03317 0.02413 0.0201 1.0000 1.0000
2.750 0.0538 0.03337 0.02442 0.0224 1.0000 1.0000
3.000 0.1659 0.03489 0.02618 0.0050 0.9635 1.0000
3.250 0.2969 0.03488 0.02651 -0.0127 0.9124 1.0000
3.500 0.4877 0.03102 0.02327 -0.0349 0.8486 1.0000
3.750 0.5814 0.02654 0.01923 -0.0386 0.7740 1.0000
4.000 0.6185 0.02388 0.01550 -0.0315 0.5183 1.0000
4.250 0.6288 0.02585 0.01599 -0.0276 0.3845 1.0000
4.500 0.6493 0.02723 0.01685 -0.0264 0.3297 1.0000
4.750 0.6727 0.02834 0.01772 -0.0257 0.2957 1.0000
5.000 0.6981 0.02949 0.01860 -0.0254 0.2723 1.0000
5.250 0.7206 0.03061 0.01966 -0.0246 0.2541 1.0000
5.500 0.7420 0.03178 0.02080 -0.0238 0.2398 1.0000
5.750 0.7598 0.03298 0.02217 -0.0223 0.2281 1.0000
6.000 0.7787 0.03442 0.02364 -0.0211 0.2189 1.0000
6.250 0.7942 0.03574 0.02512 -0.0193 0.2102 1.0000
6.500 0.8101 0.03742 0.02686 -0.0178 0.2036 1.0000
6.750 0.8197 0.03902 0.02884 -0.0151 0.1980 1.0000
7.000 0.8327 0.04056 0.03044 -0.0132 0.1921 1.0000
7.250 0.8430 0.04260 0.03258 -0.0110 0.1879 1.0000
7.500 0.8439 0.04455 0.03498 -0.0073 0.1854 1.0000
7.750 0.8450 0.04669 0.03750 -0.0041 0.1826 1.0000
8.000 0.8507 0.04908 0.04022 -0.0019 0.1793 1.0000
8.250 0.8621 0.05174 0.04310 -0.0008 0.1762 1.0000
8.500 0.8747 0.05500 0.04658 -0.0003 0.1744 1.0000
8.750 0.8890 0.05888 0.05057 -0.0004 0.1723 1.0000
9.000 0.8872 0.06311 0.05526 0.0006 0.1720 1.0000
9.250 0.8854 0.06780 0.06029 0.0009 0.1722 1.0000
9.500 0.8008 0.07711 0.07045 0.0017 0.1844 1.0000
9.750 0.7926 0.08322 0.07667 -0.0002 0.1873 1.0000
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Polar data table (+)
Polar graphs
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