NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 1,000,000 Max Cl/Cd: 39.87 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20403-il-1000000-n5.txt Download as CSV file: xf-sc20403-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5516 0.08066 0.07916 0.0099 1.0000 0.0051
-7.750 -0.5524 0.07639 0.07491 0.0084 1.0000 0.0051
-7.500 -0.5539 0.07216 0.07069 0.0066 1.0000 0.0051
-7.250 -0.5554 0.06776 0.06630 0.0038 1.0000 0.0051
-7.000 -0.5510 0.06212 0.06066 -0.0026 1.0000 0.0051
-6.750 -0.5432 0.05626 0.05476 -0.0085 1.0000 0.0051
-6.500 -0.5328 0.05055 0.04899 -0.0130 1.0000 0.0051
-6.250 -0.5198 0.04498 0.04334 -0.0167 1.0000 0.0052
-6.000 -0.5045 0.03959 0.03785 -0.0197 1.0000 0.0052
-5.750 -0.4870 0.03446 0.03258 -0.0222 1.0000 0.0052
-5.500 -0.4678 0.02957 0.02755 -0.0241 1.0000 0.0052
-5.250 -0.4467 0.02501 0.02281 -0.0257 1.0000 0.0052
-5.000 -0.4239 0.02076 0.01836 -0.0270 1.0000 0.0052
-4.750 -0.3996 0.01698 0.01435 -0.0281 1.0000 0.0052
-4.500 -0.3739 0.01360 0.01071 -0.0290 1.0000 0.0052
-4.250 -0.3468 0.01067 0.00750 -0.0298 1.0000 0.0052
-4.000 -0.3187 0.00819 0.00471 -0.0306 1.0000 0.0052
-3.500 -0.2611 0.01227 0.00748 -0.0340 1.0000 0.0035
-3.250 -0.2300 0.00974 0.00465 -0.0341 1.0000 0.0028
-3.000 -0.1987 0.00806 0.00274 -0.0346 1.0000 0.0024
-2.750 -0.1688 0.00729 0.00182 -0.0350 1.0000 0.0022
-2.500 -0.1399 0.00687 0.00128 -0.0352 1.0000 0.0023
-2.250 -0.1117 0.00662 0.00096 -0.0352 1.0000 0.0026
-2.000 -0.0842 0.00648 0.00080 -0.0352 1.0000 0.0033
-1.750 -0.0569 0.00637 0.00071 -0.0351 1.0000 0.0043
-1.500 -0.0289 0.00604 0.00062 -0.0354 1.0000 0.0649
-1.250 0.0033 0.00454 0.00049 -0.0376 1.0000 0.4992
-1.000 0.0315 0.00410 0.00050 -0.0380 1.0000 0.6434
-0.750 0.0586 0.00398 0.00052 -0.0379 1.0000 0.6831
-0.500 0.0856 0.00384 0.00056 -0.0378 1.0000 0.7338
-0.250 0.1261 0.00372 0.00058 -0.0407 0.9835 0.7719
0.000 0.1514 0.00515 0.00065 -0.0400 0.5525 0.7933
0.500 0.2031 0.00713 0.00092 -0.0402 0.0043 0.8258
0.750 0.2304 0.00720 0.00102 -0.0401 0.0033 0.8413
1.000 0.2577 0.00731 0.00118 -0.0399 0.0025 0.8556
1.250 0.2850 0.00750 0.00149 -0.0396 0.0022 0.8682
1.500 0.3122 0.00783 0.00196 -0.0393 0.0022 0.8802
2.000 0.3648 0.00966 0.00420 -0.0379 0.0026 0.9057
2.250 0.3900 0.01166 0.00648 -0.0364 0.0031 0.9210
2.500 0.4149 0.01425 0.00946 -0.0347 0.0040 0.9416
2.750 0.4396 0.01757 0.01337 -0.0330 0.0047 1.0000
3.000 0.4657 0.02189 0.01813 -0.0322 0.0051 1.0000
3.250 0.4921 0.02503 0.02156 -0.0316 0.0051 1.0000
3.500 0.5180 0.02837 0.02518 -0.0311 0.0051 1.0000
3.750 0.5433 0.03194 0.02901 -0.0306 0.0051 1.0000
4.000 0.5680 0.03575 0.03305 -0.0303 0.0051 1.0000
4.250 0.5922 0.03977 0.03728 -0.0302 0.0051 1.0000
4.500 0.6158 0.04395 0.04166 -0.0304 0.0051 1.0000
4.750 0.6388 0.04832 0.04620 -0.0309 0.0050 1.0000
5.000 0.6610 0.05287 0.05091 -0.0319 0.0050 1.0000
5.250 0.6822 0.05760 0.05577 -0.0333 0.0050 1.0000
5.500 0.7022 0.06248 0.06077 -0.0352 0.0050 1.0000
5.750 0.7210 0.06750 0.06589 -0.0377 0.0050 1.0000
6.000 0.7383 0.07262 0.07110 -0.0407 0.0049 1.0000
6.250 0.7540 0.07781 0.07636 -0.0443 0.0049 1.0000
6.500 0.7678 0.08303 0.08163 -0.0484 0.0049 1.0000
6.750 0.7798 0.08825 0.08688 -0.0529 0.0049 1.0000
7.000 0.7897 0.09339 0.09204 -0.0577 0.0048 1.0000
7.250 0.7974 0.09841 0.09707 -0.0627 0.0048 1.0000
7.500 0.7989 0.10285 0.10150 -0.0666 0.0048 1.0000
7.750 0.8004 0.10703 0.10566 -0.0694 0.0048 1.0000
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Polar data table (+)
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