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SG6043 (sg6043-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 500,000
Max Cl/Cd: 129.77 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6043-il-500000-n5.txt
Download as CSV file: xf-sg6043-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6043                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0393   0.08498   0.08256  -0.0928   0.9540   0.0143
  -9.500  -0.0317   0.08113   0.07870  -0.0949   0.9517   0.0143
  -9.250  -0.1161   0.09556   0.09302  -0.0874   0.9662   0.0130
  -8.750  -0.1041   0.08646   0.08393  -0.0935   0.9564   0.0114
  -8.500  -0.0918   0.08341   0.08088  -0.0956   0.9527   0.0112
  -8.250  -0.0801   0.08060   0.07807  -0.0977   0.9484   0.0107
  -8.000  -0.0730   0.07698   0.07445  -0.1000   0.9412   0.0107
  -7.750  -0.0588   0.07268   0.07015  -0.1047   0.9376   0.0107
  -7.500  -0.0495   0.06866   0.06612  -0.1084   0.9299   0.0107
  -7.250  -0.0324   0.06365   0.06110  -0.1153   0.9245   0.0107
  -6.750   0.0045   0.02296   0.01917  -0.1683   0.8955   0.0113
  -6.500   0.0295   0.01845   0.01387  -0.1714   0.8886   0.0116
  -6.250   0.0576   0.01671   0.01184  -0.1727   0.8830   0.0118
  -5.750   0.1149   0.01469   0.00939  -0.1743   0.8725   0.0124
  -5.500   0.1436   0.01385   0.00836  -0.1749   0.8670   0.0127
  -5.250   0.1736   0.01312   0.00744  -0.1756   0.8623   0.0130
  -5.000   0.2003   0.01258   0.00676  -0.1755   0.8566   0.0136
  -4.750   0.2288   0.01206   0.00610  -0.1758   0.8514   0.0141
  -4.500   0.2583   0.01157   0.00546  -0.1762   0.8469   0.0143
  -4.250   0.2851   0.01103   0.00486  -0.1761   0.8414   0.0146
  -4.000   0.3132   0.01057   0.00434  -0.1763   0.8362   0.0151
  -3.500   0.3696   0.00996   0.00364  -0.1765   0.8263   0.0161
  -3.250   0.3976   0.00972   0.00334  -0.1766   0.8209   0.0167
  -2.750   0.4538   0.00931   0.00283  -0.1766   0.8103   0.0184
  -2.500   0.4818   0.00915   0.00264  -0.1766   0.8046   0.0201
  -2.250   0.5105   0.00902   0.00246  -0.1768   0.7997   0.0222
  -2.000   0.5378   0.00887   0.00232  -0.1766   0.7941   0.0267
  -1.750   0.5657   0.00873   0.00222  -0.1766   0.7885   0.0413
  -1.500   0.5940   0.00864   0.00214  -0.1767   0.7834   0.0574
  -1.250   0.6211   0.00854   0.00210  -0.1766   0.7771   0.0761
  -1.000   0.6488   0.00844   0.00205  -0.1766   0.7708   0.1027
  -0.500   0.7038   0.00815   0.00202  -0.1766   0.7573   0.2115
  -0.250   0.7316   0.00793   0.00203  -0.1767   0.7505   0.3178
   0.000   0.7588   0.00768   0.00209  -0.1768   0.7425   0.4433
   0.250   0.7858   0.00755   0.00217  -0.1767   0.7345   0.5475
   0.500   0.8120   0.00749   0.00223  -0.1763   0.7251   0.6094
   0.750   0.8381   0.00747   0.00228  -0.1758   0.7156   0.6587
   1.250   0.8871   0.00738   0.00244  -0.1741   0.6939   0.7831
   1.500   0.9050   0.00725   0.00250  -0.1717   0.6816   0.8789
   1.750   0.9275   0.00722   0.00248  -0.1702   0.6678   1.0000
   2.000   0.9525   0.00737   0.00254  -0.1696   0.6534   1.0000
   2.250   0.9772   0.00753   0.00262  -0.1689   0.6379   1.0000
   2.500   1.0012   0.00772   0.00271  -0.1681   0.6202   1.0000
   2.750   1.0244   0.00794   0.00283  -0.1671   0.6004   1.0000
   3.250   1.0691   0.00845   0.00311  -0.1648   0.5576   1.0000
   3.500   1.0904   0.00874   0.00329  -0.1635   0.5341   1.0000
   3.750   1.1107   0.00909   0.00350  -0.1620   0.5060   1.0000
   4.000   1.1303   0.00947   0.00373  -0.1604   0.4779   1.0000
   4.250   1.1498   0.00986   0.00397  -0.1588   0.4508   1.0000
   4.500   1.1696   0.01024   0.00424  -0.1572   0.4245   1.0000
   4.750   1.1882   0.01064   0.00451  -0.1555   0.3986   1.0000
   5.000   1.2060   0.01107   0.00481  -0.1536   0.3725   1.0000
   5.250   1.2237   0.01152   0.00513  -0.1517   0.3458   1.0000
   5.500   1.2417   0.01197   0.00547  -0.1500   0.3225   1.0000
   5.750   1.2595   0.01244   0.00583  -0.1482   0.2984   1.0000
   6.000   1.2769   0.01294   0.00621  -0.1463   0.2749   1.0000
   6.250   1.2935   0.01348   0.00662  -0.1444   0.2507   1.0000
   6.500   1.3101   0.01403   0.00707  -0.1425   0.2263   1.0000
   6.750   1.3263   0.01462   0.00753  -0.1405   0.2045   1.0000
   7.000   1.3432   0.01515   0.00799  -0.1387   0.1871   1.0000
   7.250   1.3602   0.01569   0.00846  -0.1370   0.1714   1.0000
   7.500   1.3773   0.01623   0.00895  -0.1353   0.1580   1.0000
   7.750   1.3937   0.01679   0.00946  -0.1335   0.1452   1.0000
   8.000   1.4101   0.01737   0.01000  -0.1317   0.1329   1.0000
   8.250   1.4268   0.01794   0.01055  -0.1300   0.1229   1.0000
   8.500   1.4429   0.01853   0.01113  -0.1283   0.1145   1.0000
   8.750   1.4583   0.01919   0.01175  -0.1265   0.1056   1.0000
   9.000   1.4743   0.01980   0.01237  -0.1248   0.0983   1.0000
   9.250   1.4890   0.02051   0.01307  -0.1230   0.0914   1.0000
   9.500   1.5045   0.02117   0.01375  -0.1213   0.0856   1.0000
   9.750   1.5184   0.02195   0.01453  -0.1194   0.0797   1.0000
  10.000   1.5334   0.02266   0.01527  -0.1178   0.0746   1.0000
  10.250   1.5463   0.02354   0.01615  -0.1159   0.0692   1.0000
  10.500   1.5606   0.02432   0.01697  -0.1143   0.0651   1.0000
  10.750   1.5732   0.02525   0.01791  -0.1125   0.0604   1.0000
  11.000   1.5860   0.02617   0.01887  -0.1107   0.0566   1.0000
  11.250   1.5982   0.02716   0.01989  -0.1090   0.0526   1.0000
  11.500   1.6093   0.02825   0.02100  -0.1073   0.0491   1.0000
  11.750   1.6213   0.02929   0.02210  -0.1057   0.0462   1.0000
  12.000   1.6319   0.03047   0.02331  -0.1040   0.0435   1.0000
  12.250   1.6418   0.03172   0.02461  -0.1023   0.0413   1.0000
  12.500   1.6526   0.03292   0.02589  -0.1008   0.0393   1.0000
  12.750   1.6621   0.03427   0.02729  -0.0992   0.0372   1.0000
  13.000   1.6699   0.03580   0.02886  -0.0976   0.0352   1.0000
  13.250   1.6790   0.03723   0.03038  -0.0962   0.0337   1.0000
  13.500   1.6876   0.03874   0.03197  -0.0948   0.0321   1.0000
  13.750   1.6948   0.04043   0.03374  -0.0934   0.0306   1.0000
  14.000   1.7004   0.04232   0.03569  -0.0921   0.0292   1.0000
  14.250   1.7074   0.04412   0.03758  -0.0909   0.0280   1.0000
  14.500   1.7138   0.04601   0.03957  -0.0898   0.0268   1.0000
  14.750   1.7189   0.04810   0.04174  -0.0887   0.0256   1.0000
  15.000   1.7225   0.05041   0.04412  -0.0877   0.0244   1.0000
  15.250   1.7256   0.05285   0.04665  -0.0868   0.0235   1.0000
  15.500   1.7298   0.05522   0.04914  -0.0861   0.0225   1.0000
  15.750   1.7326   0.05782   0.05184  -0.0855   0.0215   1.0000
  16.000   1.7339   0.06067   0.05478  -0.0850   0.0206   1.0000
  16.250   1.7334   0.06384   0.05804  -0.0847   0.0197   1.0000
  16.500   1.7336   0.06702   0.06133  -0.0845   0.0190   1.0000
  16.750   1.7337   0.07028   0.06471  -0.0845   0.0183   1.0000
  17.000   1.7325   0.07381   0.06835  -0.0846   0.0176   1.0000
  17.250   1.7299   0.07762   0.07229  -0.0850   0.0170   1.0000
  17.500   1.7257   0.08179   0.07656  -0.0856   0.0165   1.0000
  17.750   1.7195   0.08639   0.08128  -0.0865   0.0160   1.0000
  18.000   1.7142   0.09094   0.08595  -0.0876   0.0156   1.0000
  18.250   1.7091   0.09553   0.09069  -0.0888   0.0152   1.0000
  18.500   1.7025   0.10047   0.09577  -0.0904   0.0148   1.0000
  18.750   1.6955   0.10558   0.10102  -0.0921   0.0144   1.0000
  19.000   1.6873   0.11100   0.10658  -0.0942   0.0141   1.0000
  19.250   1.6781   0.11668   0.11238  -0.0966   0.0139   1.0000
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