NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il) Reynolds number: 50,000 Max Cl/Cd: 18.03 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20403-il-50000.txt Download as CSV file: xf-sc20403-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7061 0.12513 0.11846 0.0284 1.0000 0.1407
-9.000 -0.6924 0.11938 0.11255 0.0302 1.0000 0.1488
-8.750 -0.7010 0.11750 0.11077 0.0261 1.0000 0.1538
-8.500 -0.6885 0.11224 0.10552 0.0277 1.0000 0.1638
-8.250 -0.6888 0.10862 0.10198 0.0259 1.0000 0.1703
-8.000 -0.6920 0.10595 0.09939 0.0231 1.0000 0.1798
-7.750 -0.6843 0.10158 0.09506 0.0236 1.0000 0.1916
-7.500 -0.6792 0.09762 0.09114 0.0227 1.0000 0.2043
-7.250 -0.6773 0.09401 0.08760 0.0191 1.0000 0.2191
-7.000 -0.6670 0.08983 0.08345 0.0221 1.0000 0.2415
-6.750 -0.6614 0.08626 0.07994 0.0224 1.0000 0.2690
-6.500 -0.6542 0.08276 0.07649 0.0252 1.0000 0.3044
-6.250 -0.6493 0.07987 0.07366 0.0280 1.0000 0.3498
-6.000 -0.6427 0.07705 0.07090 0.0335 1.0000 0.4034
-5.750 -0.6251 0.07350 0.06737 0.0426 1.0000 0.4649
-4.500 -0.4346 0.03880 0.02990 -0.0310 1.0000 0.1526
-4.250 -0.3924 0.03490 0.02485 -0.0326 1.0000 0.1148
-4.000 -0.3594 0.03129 0.02068 -0.0328 1.0000 0.1004
-3.750 -0.3273 0.02805 0.01659 -0.0325 1.0000 0.0918
-3.500 -0.2955 0.02593 0.01380 -0.0317 1.0000 0.0886
-3.250 -0.2678 0.02341 0.01113 -0.0305 1.0000 0.0902
-3.000 -0.2431 0.02143 0.00919 -0.0291 1.0000 0.1069
-2.750 -0.2168 0.01968 0.00734 -0.0277 1.0000 0.1273
-2.500 -0.1873 0.01695 0.00523 -0.0278 1.0000 0.2090
-2.250 -0.1866 0.01347 0.00436 -0.0167 1.0000 1.0000
-2.000 -0.1589 0.01336 0.00356 -0.0167 1.0000 1.0000
-1.750 -0.1314 0.01327 0.00301 -0.0169 1.0000 1.0000
-1.500 -0.1039 0.01320 0.00261 -0.0172 1.0000 1.0000
-1.250 -0.0765 0.01315 0.00230 -0.0173 1.0000 1.0000
-1.000 -0.0492 0.01311 0.00200 -0.0175 1.0000 1.0000
-0.750 -0.0219 0.01309 0.00183 -0.0176 1.0000 1.0000
-0.500 0.0052 0.01309 0.00173 -0.0177 1.0000 1.0000
-0.250 0.0322 0.01310 0.00169 -0.0177 1.0000 1.0000
0.000 0.0591 0.01312 0.00173 -0.0177 1.0000 1.0000
0.250 0.0860 0.01315 0.00183 -0.0177 1.0000 1.0000
0.500 0.1127 0.01319 0.00200 -0.0176 1.0000 1.0000
0.750 0.1394 0.01325 0.00224 -0.0175 1.0000 1.0000
1.000 0.1661 0.01333 0.00262 -0.0174 1.0000 1.0000
1.250 0.1926 0.01341 0.00301 -0.0172 1.0000 1.0000
1.500 0.2192 0.01352 0.00352 -0.0170 1.0000 1.0000
1.750 0.2459 0.01364 0.00423 -0.0167 1.0000 1.0000
2.000 0.3088 0.01939 0.00721 -0.0203 0.1293 1.0000
2.250 0.3393 0.02141 0.00932 -0.0195 0.1104 1.0000
2.500 0.3693 0.02356 0.01146 -0.0192 0.0892 1.0000
2.750 0.4002 0.02619 0.01431 -0.0185 0.0875 1.0000
3.000 0.4322 0.02841 0.01717 -0.0176 0.0908 1.0000
3.250 0.4638 0.03155 0.02087 -0.0169 0.0989 1.0000
3.500 0.4955 0.03521 0.02540 -0.0163 0.1137 1.0000
3.750 0.5338 0.03874 0.03008 -0.0162 0.1507 1.0000
4.000 0.6438 0.05337 0.04774 -0.0983 0.7359 1.0000
4.250 0.6150 0.05564 0.04983 -0.1002 0.7999 1.0000
4.500 0.6009 0.05805 0.05214 -0.0998 0.8271 1.0000
5.500 0.7469 0.07596 0.07044 -0.0596 0.3601 1.0000
5.750 0.7536 0.07947 0.07387 -0.0538 0.3085 1.0000
6.000 0.7597 0.08320 0.07754 -0.0511 0.2687 1.0000
6.250 0.7656 0.08703 0.08135 -0.0510 0.2383 1.0000
6.500 0.7728 0.09139 0.08566 -0.0504 0.2164 1.0000
6.750 0.7774 0.09545 0.08971 -0.0528 0.1990 1.0000
7.000 0.7822 0.09975 0.09398 -0.0547 0.1860 1.0000
7.250 0.7868 0.10419 0.09839 -0.0564 0.1759 1.0000
7.500 0.7957 0.10914 0.10331 -0.0555 0.1656 1.0000
7.750 0.7900 0.11219 0.10629 -0.0605 0.1584 1.0000
8.000 0.7955 0.11695 0.11102 -0.0609 0.1517 1.0000
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Polar data table (+)
Polar graphs
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