NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 50,000 Max Cl/Cd: 22.37 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20410-il-50000.txt Download as CSV file: xf-sc20410-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0410 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5479 0.10302 0.09535 0.0131 1.0000 0.3991
-8.250 -0.6956 0.07259 0.06506 -0.0292 1.0000 0.1740
-8.000 -0.7124 0.06433 0.05643 -0.0340 1.0000 0.1578
-7.750 -0.7212 0.05689 0.04812 -0.0378 1.0000 0.1454
-7.500 -0.7067 0.05231 0.04333 -0.0381 1.0000 0.1437
-7.250 -0.6922 0.04803 0.03856 -0.0389 1.0000 0.1441
-7.000 -0.6736 0.04415 0.03401 -0.0397 1.0000 0.1454
-6.750 -0.6519 0.04045 0.02996 -0.0399 1.0000 0.1472
-6.500 -0.6298 0.03786 0.02737 -0.0395 1.0000 0.1536
-6.250 -0.6047 0.03519 0.02416 -0.0396 1.0000 0.1596
-6.000 -0.5808 0.03274 0.02163 -0.0391 1.0000 0.1671
-5.750 -0.5548 0.03080 0.01925 -0.0388 1.0000 0.1769
-5.500 -0.5315 0.02889 0.01746 -0.0376 1.0000 0.1876
-5.250 -0.5079 0.02730 0.01589 -0.0363 1.0000 0.2018
-5.000 -0.4852 0.02589 0.01454 -0.0344 1.0000 0.2183
-4.750 -0.4634 0.02457 0.01337 -0.0326 1.0000 0.2430
-4.500 -0.4427 0.02307 0.01224 -0.0308 1.0000 0.2817
-4.250 -0.4268 0.02029 0.01101 -0.0290 1.0000 0.4138
-4.000 -0.4366 0.02318 0.01515 -0.0130 1.0000 0.6779
-3.750 -0.4346 0.02529 0.01709 -0.0023 1.0000 0.7400
-3.500 -0.4291 0.02643 0.01807 0.0070 1.0000 0.7814
-3.250 -0.4176 0.02689 0.01836 0.0143 1.0000 0.8213
-3.000 -0.3924 0.02688 0.01812 0.0189 1.0000 0.8657
-2.750 -0.1379 0.02496 0.01493 -0.0171 1.0000 0.9818
-2.500 -0.0716 0.02362 0.01336 -0.0262 1.0000 1.0000
-2.250 -0.0573 0.02312 0.01282 -0.0252 1.0000 1.0000
-2.000 -0.0436 0.02269 0.01235 -0.0241 1.0000 1.0000
-1.750 -0.0306 0.02232 0.01196 -0.0227 1.0000 1.0000
-1.500 -0.0184 0.02200 0.01164 -0.0211 1.0000 1.0000
-1.250 -0.0072 0.02172 0.01138 -0.0193 1.0000 1.0000
-1.000 0.0033 0.02149 0.01116 -0.0173 1.0000 1.0000
-0.750 0.0127 0.02129 0.01099 -0.0151 1.0000 1.0000
-0.500 0.0210 0.02113 0.01087 -0.0127 1.0000 1.0000
-0.250 0.0280 0.02100 0.01079 -0.0101 1.0000 1.0000
0.000 0.0338 0.02090 0.01074 -0.0073 1.0000 1.0000
0.250 0.0385 0.02082 0.01071 -0.0043 1.0000 1.0000
0.500 0.0423 0.02075 0.01070 -0.0013 1.0000 1.0000
0.750 0.0452 0.02070 0.01070 0.0018 1.0000 1.0000
1.000 0.0477 0.02064 0.01072 0.0050 1.0000 1.0000
1.250 0.0500 0.02060 0.01074 0.0081 1.0000 1.0000
1.500 0.0527 0.02056 0.01078 0.0110 1.0000 1.0000
1.750 0.0582 0.02057 0.01087 0.0133 1.0000 1.0000
2.000 0.0698 0.02067 0.01107 0.0145 1.0000 1.0000
2.250 0.0867 0.02088 0.01139 0.0146 1.0000 1.0000
2.500 0.1071 0.02120 0.01183 0.0141 1.0000 1.0000
2.750 0.1299 0.02163 0.01242 0.0130 1.0000 1.0000
3.000 0.1539 0.02216 0.01312 0.0115 1.0000 1.0000
3.250 0.1787 0.02282 0.01397 0.0097 1.0000 1.0000
3.500 0.2176 0.02376 0.01520 0.0053 0.9933 1.0000
4.000 0.4898 0.02190 0.01166 -0.0123 0.3252 1.0000
4.250 0.5121 0.02360 0.01291 -0.0113 0.2655 1.0000
4.500 0.5393 0.02507 0.01415 -0.0111 0.2320 1.0000
4.750 0.5684 0.02669 0.01566 -0.0111 0.2112 1.0000
5.000 0.5954 0.02833 0.01734 -0.0110 0.1945 1.0000
5.250 0.6237 0.03034 0.01935 -0.0112 0.1825 1.0000
5.500 0.6501 0.03216 0.02149 -0.0111 0.1712 1.0000
5.750 0.6770 0.03465 0.02432 -0.0112 0.1639 1.0000
6.000 0.7031 0.03699 0.02691 -0.0113 0.1554 1.0000
6.250 0.7284 0.04020 0.03045 -0.0116 0.1514 1.0000
6.500 0.7493 0.04340 0.03435 -0.0113 0.1477 1.0000
6.750 0.7690 0.04723 0.03874 -0.0113 0.1467 1.0000
7.000 0.7864 0.05170 0.04371 -0.0115 0.1486 1.0000
7.250 0.8019 0.05638 0.04880 -0.0120 0.1502 1.0000
7.500 0.8181 0.06133 0.05400 -0.0126 0.1520 1.0000
7.750 0.7946 0.07254 0.06640 -0.0179 0.1902 1.0000
8.000 0.6658 0.10022 0.09440 -0.0614 0.4130 1.0000
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Polar data table (+)
Polar graphs
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