NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 500,000 Max Cl/Cd: 33.23 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20403-il-500000-n5.txt Download as CSV file: xf-sc20403-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0403 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6784 0.11909 0.11679 0.0307 1.0000 0.0052
-9.250 -0.6743 0.11510 0.11281 0.0290 1.0000 0.0052
-9.000 -0.6702 0.11110 0.10882 0.0272 1.0000 0.0052
-8.750 -0.6662 0.10710 0.10483 0.0253 1.0000 0.0052
-8.500 -0.6622 0.10310 0.10085 0.0233 1.0000 0.0052
-8.250 -0.6582 0.09908 0.09685 0.0211 1.0000 0.0052
-8.000 -0.6543 0.09504 0.09282 0.0187 1.0000 0.0052
-7.750 -0.6499 0.09087 0.08868 0.0156 1.0000 0.0052
-7.500 -0.6405 0.08601 0.08383 0.0103 1.0000 0.0052
-7.250 -0.6280 0.08062 0.07843 0.0036 1.0000 0.0053
-7.000 -0.6135 0.07517 0.07293 -0.0025 1.0000 0.0053
-6.750 -0.5975 0.06983 0.06753 -0.0076 1.0000 0.0053
-6.500 -0.5801 0.06460 0.06221 -0.0121 1.0000 0.0053
-6.250 -0.5610 0.05948 0.05699 -0.0158 1.0000 0.0053
-6.000 -0.5405 0.05452 0.05189 -0.0190 1.0000 0.0053
-5.750 -0.5203 0.04763 0.04481 -0.0228 1.0000 0.0054
-5.500 -0.4975 0.04142 0.03835 -0.0258 1.0000 0.0056
-5.250 -0.4722 0.03637 0.03303 -0.0279 1.0000 0.0058
-5.000 -0.4451 0.03200 0.02836 -0.0295 1.0000 0.0059
-4.750 -0.4164 0.02821 0.02426 -0.0305 1.0000 0.0059
-4.250 -0.3588 0.02319 0.01874 -0.0315 1.0000 0.0049
-4.000 -0.3271 0.01905 0.01412 -0.0325 1.0000 0.0045
-3.750 -0.2960 0.01607 0.01072 -0.0328 1.0000 0.0041
-3.500 -0.2657 0.01367 0.00781 -0.0329 1.0000 0.0037
-3.250 -0.2360 0.01172 0.00559 -0.0329 1.0000 0.0035
-3.000 -0.2065 0.01019 0.00387 -0.0330 1.0000 0.0034
-2.750 -0.1766 0.00909 0.00262 -0.0334 1.0000 0.0034
-2.500 -0.1471 0.00839 0.00177 -0.0337 1.0000 0.0036
-2.250 -0.1186 0.00802 0.00127 -0.0338 1.0000 0.0044
-2.000 -0.0909 0.00782 0.00102 -0.0337 1.0000 0.0065
-1.750 -0.0591 0.00622 0.00078 -0.0360 1.0000 0.3791
-1.500 -0.0301 0.00534 0.00076 -0.0368 1.0000 0.6373
-1.250 -0.0036 0.00503 0.00078 -0.0365 1.0000 0.7360
-1.000 0.0220 0.00490 0.00082 -0.0359 1.0000 0.7891
-0.750 0.0475 0.00481 0.00084 -0.0352 1.0000 0.8236
-0.500 0.0730 0.00476 0.00086 -0.0346 1.0000 0.8459
-0.250 0.0985 0.00471 0.00090 -0.0341 1.0000 0.8637
0.000 0.1236 0.00467 0.00095 -0.0334 1.0000 0.8814
0.250 0.1480 0.00462 0.00101 -0.0325 1.0000 0.8998
0.750 0.2108 0.00779 0.00116 -0.0347 0.0736 0.9252
1.000 0.2343 0.00817 0.00128 -0.0337 0.0049 0.9493
1.250 0.2621 0.00834 0.00155 -0.0335 0.0039 1.0000
1.500 0.2906 0.00881 0.00215 -0.0336 0.0034 1.0000
1.750 0.3187 0.00959 0.00307 -0.0334 0.0032 1.0000
2.000 0.3462 0.01079 0.00442 -0.0331 0.0033 1.0000
2.250 0.3739 0.01237 0.00619 -0.0325 0.0034 1.0000
2.500 0.4021 0.01441 0.00850 -0.0319 0.0037 1.0000
2.750 0.4305 0.01679 0.01139 -0.0312 0.0040 1.0000
3.000 0.4585 0.01968 0.01470 -0.0305 0.0044 1.0000
3.250 0.4850 0.02376 0.01925 -0.0298 0.0049 1.0000
5.750 0.7073 0.06756 0.06532 -0.0352 0.0051 1.0000
6.000 0.7240 0.07268 0.07054 -0.0379 0.0051 1.0000
6.250 0.7391 0.07787 0.07581 -0.0411 0.0051 1.0000
6.500 0.7526 0.08308 0.08108 -0.0448 0.0051 1.0000
6.750 0.7643 0.08830 0.08634 -0.0489 0.0051 1.0000
7.000 0.7742 0.09345 0.09153 -0.0533 0.0051 1.0000
7.250 0.7821 0.09852 0.09661 -0.0580 0.0051 1.0000
7.500 0.7856 0.10314 0.10122 -0.0621 0.0051 1.0000
7.750 0.7874 0.10750 0.10556 -0.0651 0.0051 1.0000
8.000 0.7896 0.11179 0.10984 -0.0676 0.0051 1.0000
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Polar data table (+)
Polar graphs
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