NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il) Reynolds number: 50,000 Max Cl/Cd: 23.7 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20010-il-50000.txt Download as CSV file: xf-sc20010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0010 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6003 0.10908 0.10170 0.0260 1.0000 0.3644
-8.750 -0.6137 0.10686 0.09956 0.0264 1.0000 0.3830
-8.000 -0.7609 0.06810 0.06027 -0.0140 1.0000 0.1686
-7.750 -0.7570 0.06148 0.05337 -0.0145 1.0000 0.1566
-7.500 -0.7482 0.05651 0.04807 -0.0143 1.0000 0.1499
-7.250 -0.7403 0.05173 0.04286 -0.0137 1.0000 0.1461
-7.000 -0.7286 0.04781 0.03849 -0.0128 1.0000 0.1465
-6.750 -0.7137 0.04429 0.03453 -0.0118 1.0000 0.1483
-6.500 -0.6963 0.04092 0.03065 -0.0108 1.0000 0.1498
-6.250 -0.6777 0.03813 0.02714 -0.0095 1.0000 0.1542
-6.000 -0.6548 0.03548 0.02455 -0.0089 1.0000 0.1613
-5.750 -0.6323 0.03328 0.02175 -0.0077 1.0000 0.1690
-5.500 -0.6077 0.03109 0.01963 -0.0071 1.0000 0.1794
-5.250 -0.5828 0.02918 0.01761 -0.0064 1.0000 0.1916
-5.000 -0.5568 0.02742 0.01580 -0.0057 1.0000 0.2058
-4.750 -0.5306 0.02587 0.01426 -0.0049 1.0000 0.2257
-4.500 -0.5037 0.02428 0.01288 -0.0042 1.0000 0.2505
-4.250 -0.4792 0.02269 0.01155 -0.0031 1.0000 0.2919
-4.000 -0.4633 0.02040 0.01023 -0.0009 1.0000 0.3843
-3.750 -0.4674 0.01972 0.01175 0.0114 1.0000 0.7503
-3.500 -0.3943 0.02294 0.01444 0.0145 1.0000 0.8826
-3.250 -0.1490 0.02362 0.01376 -0.0204 1.0000 1.0000
-3.000 -0.1308 0.02292 0.01294 -0.0205 1.0000 1.0000
-2.750 -0.1124 0.02231 0.01222 -0.0204 1.0000 1.0000
-2.500 -0.0939 0.02178 0.01160 -0.0202 1.0000 1.0000
-2.250 -0.0756 0.02131 0.01106 -0.0198 1.0000 1.0000
-2.000 -0.0577 0.02090 0.01061 -0.0193 1.0000 1.0000
-1.750 -0.0405 0.02055 0.01022 -0.0186 1.0000 1.0000
-1.500 -0.0247 0.02026 0.00991 -0.0176 1.0000 1.0000
-1.250 -0.0108 0.02003 0.00968 -0.0163 1.0000 1.0000
-1.000 -0.0003 0.01986 0.00954 -0.0144 1.0000 1.0000
-0.750 0.0055 0.01978 0.00948 -0.0117 1.0000 1.0000
-0.500 0.0066 0.01976 0.00948 -0.0083 1.0000 1.0000
-0.250 0.0042 0.01977 0.00950 -0.0043 1.0000 1.0000
0.000 0.0000 0.01977 0.00951 0.0000 1.0000 1.0000
0.250 -0.0042 0.01976 0.00950 0.0043 1.0000 1.0000
0.500 -0.0066 0.01976 0.00948 0.0083 1.0000 1.0000
0.750 -0.0055 0.01978 0.00948 0.0117 1.0000 1.0000
1.000 0.0003 0.01986 0.00954 0.0144 1.0000 1.0000
1.250 0.0109 0.02002 0.00968 0.0163 1.0000 1.0000
1.500 0.0247 0.02025 0.00991 0.0176 1.0000 1.0000
1.750 0.0406 0.02055 0.01021 0.0186 1.0000 1.0000
2.000 0.0577 0.02090 0.01060 0.0193 1.0000 1.0000
2.250 0.0757 0.02131 0.01106 0.0198 1.0000 1.0000
2.500 0.0940 0.02177 0.01159 0.0201 1.0000 1.0000
2.750 0.1125 0.02231 0.01221 0.0203 1.0000 1.0000
3.000 0.1310 0.02291 0.01293 0.0204 1.0000 1.0000
3.250 0.1492 0.02361 0.01375 0.0204 1.0000 1.0000
3.500 0.3943 0.02293 0.01443 -0.0146 0.8826 1.0000
3.750 0.4673 0.01972 0.01175 -0.0114 0.7504 1.0000
4.000 0.4633 0.02039 0.01023 0.0009 0.3843 1.0000
4.250 0.4792 0.02269 0.01155 0.0031 0.2919 1.0000
4.500 0.5037 0.02428 0.01287 0.0042 0.2505 1.0000
4.750 0.5306 0.02587 0.01426 0.0049 0.2257 1.0000
5.000 0.5568 0.02742 0.01580 0.0057 0.2059 1.0000
5.250 0.5828 0.02918 0.01763 0.0064 0.1916 1.0000
5.500 0.6076 0.03109 0.01963 0.0072 0.1794 1.0000
5.750 0.6323 0.03328 0.02175 0.0078 0.1690 1.0000
6.000 0.6548 0.03548 0.02454 0.0089 0.1613 1.0000
6.250 0.6777 0.03813 0.02714 0.0095 0.1542 1.0000
6.500 0.6963 0.04092 0.03065 0.0107 0.1498 1.0000
6.750 0.7137 0.04430 0.03453 0.0118 0.1483 1.0000
7.000 0.7286 0.04781 0.03849 0.0128 0.1465 1.0000
7.250 0.7403 0.05174 0.04286 0.0137 0.1462 1.0000
7.500 0.7483 0.05652 0.04807 0.0143 0.1499 1.0000
7.750 0.7572 0.06148 0.05337 0.0145 0.1566 1.0000
8.000 0.7368 0.07017 0.06273 0.0121 0.1788 1.0000
8.250 0.5849 0.09866 0.09134 -0.0282 0.4174 1.0000
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Polar data table (+)
Polar graphs
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