NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 1,000,000 Max Cl/Cd: 42.82 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20503-il-1000000-n5.txt Download as CSV file: xf-sc20503-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0503 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 -0.5313 0.08372 0.08220 0.0062 1.0000 0.0051
-8.250 -0.5313 0.07955 0.07804 0.0048 1.0000 0.0051
-8.000 -0.5317 0.07538 0.07388 0.0034 1.0000 0.0051
-7.750 -0.5329 0.07124 0.06976 0.0017 1.0000 0.0051
-7.500 -0.5341 0.06697 0.06551 -0.0007 1.0000 0.0051
-7.000 -0.5797 0.06903 0.06740 -0.0118 1.0000 0.0051
-4.000 -0.2665 0.01563 0.01130 -0.0409 1.0000 0.0045
-3.750 -0.2331 0.01213 0.00736 -0.0416 1.0000 0.0034
-3.500 -0.2011 0.00950 0.00443 -0.0419 1.0000 0.0027
-3.250 -0.1691 0.00787 0.00256 -0.0426 1.0000 0.0023
-3.000 -0.1395 0.00718 0.00173 -0.0430 1.0000 0.0022
-2.750 -0.1112 0.00681 0.00125 -0.0430 1.0000 0.0023
-2.500 -0.0837 0.00660 0.00096 -0.0429 1.0000 0.0026
-2.250 -0.0569 0.00647 0.00082 -0.0427 1.0000 0.0034
-2.000 -0.0302 0.00637 0.00075 -0.0425 1.0000 0.0044
-1.750 -0.0019 0.00596 0.00067 -0.0429 1.0000 0.0894
-1.500 0.0296 0.00506 0.00057 -0.0445 1.0000 0.3563
-1.250 0.0606 0.00427 0.00056 -0.0459 1.0000 0.6056
-1.000 0.0887 0.00401 0.00063 -0.0461 1.0000 0.7064
-0.750 0.1191 0.00394 0.00065 -0.0468 0.9982 0.7314
-0.500 0.1630 0.00501 0.00061 -0.0502 0.6290 0.7592
0.000 0.2133 0.00721 0.00089 -0.0502 0.0118 0.7885
0.250 0.2409 0.00732 0.00099 -0.0502 0.0040 0.8018
0.500 0.2684 0.00742 0.00109 -0.0501 0.0030 0.8146
0.750 0.2959 0.00755 0.00130 -0.0500 0.0024 0.8275
1.250 0.3507 0.00819 0.00221 -0.0495 0.0022 0.8503
1.500 0.3775 0.00895 0.00316 -0.0490 0.0023 0.8598
1.750 0.4036 0.01065 0.00512 -0.0479 0.0027 0.8692
2.000 0.4305 0.01311 0.00788 -0.0467 0.0034 0.8793
2.250 0.4574 0.01632 0.01153 -0.0453 0.0045 0.8910
4.250 0.6466 0.04491 0.04260 -0.0384 0.0050 1.0000
4.500 0.6688 0.04921 0.04708 -0.0386 0.0050 1.0000
4.750 0.6901 0.05370 0.05173 -0.0393 0.0050 1.0000
5.000 0.7105 0.05837 0.05654 -0.0404 0.0050 1.0000
5.250 0.7297 0.06319 0.06148 -0.0420 0.0050 1.0000
5.500 0.7475 0.06816 0.06655 -0.0441 0.0049 1.0000
5.750 0.7639 0.07324 0.07172 -0.0467 0.0049 1.0000
6.000 0.7787 0.07839 0.07694 -0.0499 0.0049 1.0000
6.250 0.7918 0.08359 0.08220 -0.0536 0.0049 1.0000
6.500 0.8030 0.08879 0.08743 -0.0578 0.0048 1.0000
6.750 0.8122 0.09395 0.09262 -0.0623 0.0048 1.0000
7.000 0.8192 0.09899 0.09767 -0.0671 0.0048 1.0000
7.250 0.8203 0.10347 0.10214 -0.0712 0.0048 1.0000
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Polar data table (+)
Polar graphs
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