NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 50,000 Max Cl/Cd: 20.89 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20406-il-50000.txt Download as CSV file: xf-sc20406-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0406 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6483 0.09906 0.09234 0.0260 1.0000 0.3189
-7.750 -0.6305 0.09454 0.08780 0.0280 1.0000 0.3395
-7.500 -0.6388 0.09220 0.08558 0.0282 1.0000 0.3623
-7.250 -0.6333 0.08916 0.08257 0.0300 1.0000 0.3891
-6.250 -0.5927 0.05174 0.04379 -0.0276 1.0000 0.1513
-6.000 -0.5625 0.04515 0.03622 -0.0311 1.0000 0.1244
-5.750 -0.5364 0.04034 0.03096 -0.0320 1.0000 0.1171
-5.500 -0.5081 0.03646 0.02645 -0.0329 1.0000 0.1166
-5.250 -0.4795 0.03329 0.02274 -0.0333 1.0000 0.1211
-5.000 -0.4493 0.03021 0.01904 -0.0333 1.0000 0.1236
-4.750 -0.4216 0.02759 0.01619 -0.0330 1.0000 0.1358
-4.500 -0.3937 0.02521 0.01358 -0.0322 1.0000 0.1512
-4.250 -0.3681 0.02314 0.01151 -0.0311 1.0000 0.1786
-4.000 -0.3434 0.02119 0.00966 -0.0294 1.0000 0.2090
-3.750 -0.3191 0.01882 0.00797 -0.0288 1.0000 0.2904
-3.500 -0.3263 0.01669 0.00854 -0.0171 1.0000 0.7515
-3.250 -0.3331 0.01695 0.00881 -0.0045 1.0000 0.8626
-3.000 -0.1990 0.01675 0.00728 -0.0183 1.0000 1.0000
-2.750 -0.1811 0.01626 0.00659 -0.0180 1.0000 1.0000
-2.500 -0.1638 0.01583 0.00598 -0.0175 1.0000 1.0000
-2.250 -0.1472 0.01546 0.00547 -0.0167 1.0000 1.0000
-2.000 -0.1317 0.01513 0.00502 -0.0155 1.0000 1.0000
-1.750 -0.1171 0.01485 0.00461 -0.0141 1.0000 1.0000
-1.500 -0.1019 0.01462 0.00429 -0.0128 1.0000 1.0000
-1.250 -0.0835 0.01445 0.00403 -0.0119 1.0000 1.0000
-1.000 -0.0619 0.01434 0.00383 -0.0116 1.0000 1.0000
-0.750 -0.0382 0.01428 0.00368 -0.0115 1.0000 1.0000
-0.500 -0.0132 0.01425 0.00359 -0.0117 1.0000 1.0000
-0.250 0.0126 0.01426 0.00355 -0.0119 1.0000 1.0000
0.000 0.0387 0.01429 0.00357 -0.0122 1.0000 1.0000
0.250 0.0649 0.01435 0.00364 -0.0124 1.0000 1.0000
0.500 0.0911 0.01443 0.00377 -0.0127 1.0000 1.0000
0.750 0.1173 0.01454 0.00396 -0.0129 1.0000 1.0000
1.000 0.1434 0.01467 0.00419 -0.0131 1.0000 1.0000
1.250 0.1693 0.01484 0.00447 -0.0133 1.0000 1.0000
1.500 0.1952 0.01502 0.00482 -0.0134 1.0000 1.0000
1.750 0.2210 0.01525 0.00527 -0.0136 1.0000 1.0000
2.000 0.2468 0.01550 0.00575 -0.0139 1.0000 1.0000
2.250 0.2725 0.01580 0.00632 -0.0141 1.0000 1.0000
2.500 0.2980 0.01614 0.00697 -0.0144 1.0000 1.0000
2.750 0.3233 0.01653 0.00774 -0.0147 1.0000 1.0000
3.000 0.3485 0.01698 0.00874 -0.0150 1.0000 1.0000
3.250 0.4532 0.02169 0.01030 -0.0194 0.2055 1.0000
3.500 0.4848 0.02385 0.01242 -0.0190 0.1699 1.0000
3.750 0.5144 0.02611 0.01469 -0.0186 0.1439 1.0000
4.000 0.5445 0.02874 0.01763 -0.0181 0.1306 1.0000
4.250 0.5726 0.03143 0.02057 -0.0178 0.1188 1.0000
4.500 0.6020 0.03466 0.02439 -0.0173 0.1178 1.0000
4.750 0.6295 0.03829 0.02856 -0.0169 0.1190 1.0000
5.000 0.6551 0.04207 0.03289 -0.0166 0.1193 1.0000
5.250 0.6800 0.04609 0.03742 -0.0165 0.1226 1.0000
5.500 0.7071 0.05276 0.04530 -0.0182 0.1558 1.0000
6.250 0.7424 0.08430 0.07860 -0.0709 0.4400 1.0000
6.500 0.7461 0.08714 0.08139 -0.0670 0.3961 1.0000
6.750 0.7499 0.09047 0.08467 -0.0648 0.3636 1.0000
7.000 0.7551 0.09423 0.08839 -0.0633 0.3377 1.0000
7.250 0.7729 0.09876 0.09293 -0.0604 0.3146 1.0000
7.500 0.7620 0.10188 0.09596 -0.0618 0.2957 1.0000
7.750 0.7677 0.10580 0.09985 -0.0612 0.2776 1.0000
8.000 0.7778 0.11021 0.10430 -0.0600 0.2615 1.0000
8.250 0.7745 0.11390 0.10793 -0.0612 0.2486 1.0000
8.500 0.7707 0.11765 0.11162 -0.0625 0.2372 1.0000
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Polar data table (+)
Polar graphs
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