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SG6043 (sg6043-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 500,000
Max Cl/Cd: 142.98 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6043-il-500000.txt
Download as CSV file: xf-sg6043-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0664   0.09089   0.08859  -0.0846   0.9694   0.0181
  -9.500  -0.0547   0.08749   0.08518  -0.0865   0.9673   0.0183
  -9.250  -0.0426   0.08399   0.08168  -0.0887   0.9658   0.0188
  -9.000  -0.0306   0.08017   0.07787  -0.0914   0.9646   0.0193
  -8.750  -0.0186   0.07618   0.07388  -0.0944   0.9636   0.0199
  -8.500  -0.0191   0.07190   0.06960  -0.0970   0.9578   0.0212
  -8.250  -0.0147   0.06691   0.06462  -0.1016   0.9546   0.0214
  -8.000  -0.0029   0.06258   0.06029  -0.1038   0.9530   0.0217
  -7.750   0.0152   0.05963   0.05734  -0.1054   0.9518   0.0222
  -7.500   0.0310   0.05602   0.05373  -0.1086   0.9507   0.0230
  -7.000  -0.0421   0.06812   0.06575  -0.1093   0.9444   0.0220
  -6.750  -0.0209   0.06517   0.06280  -0.1129   0.9414   0.0228
  -6.500   0.0058   0.06054   0.05815  -0.1213   0.9390   0.0244
  -6.250   0.0369   0.04980   0.04732  -0.1415   0.9303   0.0260
  -6.000   0.0631   0.04820   0.04570  -0.1437   0.9279   0.0267
  -5.750   0.0980   0.04415   0.04157  -0.1515   0.9253   0.0282
  -5.500   0.1312   0.03477   0.03181  -0.1639   0.9172   0.0314
  -5.250   0.1599   0.03295   0.02992  -0.1664   0.9131   0.0323
  -5.000   0.1957   0.02939   0.02611  -0.1713   0.9098   0.0350
  -4.750   0.2236   0.01818   0.01360  -0.1758   0.9019   0.0249
  -4.500   0.2558   0.01488   0.00974  -0.1774   0.8976   0.0230
  -4.250   0.2901   0.01358   0.00816  -0.1790   0.8944   0.0234
  -4.000   0.3164   0.01275   0.00716  -0.1787   0.8887   0.0239
  -3.750   0.3456   0.01186   0.00612  -0.1789   0.8838   0.0240
  -3.500   0.3777   0.01116   0.00529  -0.1797   0.8798   0.0245
  -3.250   0.4055   0.01068   0.00474  -0.1797   0.8746   0.0252
  -3.000   0.4334   0.01021   0.00421  -0.1797   0.8690   0.0260
  -2.750   0.4646   0.00978   0.00375  -0.1804   0.8644   0.0274
  -2.500   0.4925   0.00956   0.00350  -0.1803   0.8591   0.0295
  -2.250   0.5204   0.00930   0.00323  -0.1803   0.8534   0.0330
  -2.000   0.5511   0.00903   0.00295  -0.1808   0.8489   0.0411
  -1.750   0.5791   0.00878   0.00280  -0.1808   0.8435   0.0756
  -1.500   0.6066   0.00863   0.00271  -0.1808   0.8376   0.1021
  -1.250   0.6369   0.00843   0.00262  -0.1813   0.8326   0.1508
  -1.000   0.6638   0.00812   0.00262  -0.1814   0.8265   0.2601
  -0.750   0.6919   0.00763   0.00265  -0.1818   0.8203   0.4622
  -0.500   0.7210   0.00740   0.00273  -0.1821   0.8149   0.6077
  -0.250   0.7458   0.00728   0.00279  -0.1813   0.8079   0.6771
   0.000   0.7729   0.00719   0.00280  -0.1809   0.8017   0.7381
   0.250   0.7967   0.00710   0.00285  -0.1798   0.7946   0.7993
   0.500   0.8177   0.00697   0.00285  -0.1779   0.7873   0.8717
   0.750   0.8411   0.00682   0.00277  -0.1766   0.7801   1.0000
   1.000   0.8683   0.00688   0.00276  -0.1763   0.7722   1.0000
   1.250   0.8957   0.00695   0.00277  -0.1762   0.7644   1.0000
   1.500   0.9223   0.00701   0.00277  -0.1758   0.7554   1.0000
   1.750   0.9485   0.00709   0.00280  -0.1754   0.7461   1.0000
   2.000   0.9756   0.00718   0.00281  -0.1751   0.7371   1.0000
   2.250   1.0006   0.00725   0.00287  -0.1745   0.7263   1.0000
   2.500   1.0262   0.00734   0.00292  -0.1739   0.7152   1.0000
   2.750   1.0514   0.00745   0.00296  -0.1733   0.7031   1.0000
   3.000   1.0761   0.00757   0.00302  -0.1725   0.6900   1.0000
   3.250   1.1003   0.00770   0.00311  -0.1717   0.6757   1.0000
   3.500   1.1238   0.00786   0.00321  -0.1707   0.6595   1.0000
   3.750   1.1467   0.00805   0.00332  -0.1696   0.6415   1.0000
   4.000   1.1692   0.00825   0.00345  -0.1684   0.6226   1.0000
   4.250   1.1911   0.00848   0.00360  -0.1672   0.6023   1.0000
   4.500   1.2123   0.00874   0.00379  -0.1658   0.5818   1.0000
   4.750   1.2329   0.00903   0.00399  -0.1643   0.5594   1.0000
   5.000   1.2522   0.00937   0.00422  -0.1626   0.5345   1.0000
   5.250   1.2712   0.00971   0.00447  -0.1608   0.5095   1.0000
   5.500   1.2886   0.01013   0.00476  -0.1588   0.4824   1.0000
   5.750   1.3044   0.01057   0.00507  -0.1564   0.4538   1.0000
   6.000   1.3190   0.01105   0.00541  -0.1539   0.4230   1.0000
   6.250   1.3326   0.01160   0.00581  -0.1512   0.3908   1.0000
   6.500   1.3461   0.01220   0.00624  -0.1486   0.3580   1.0000
   6.750   1.3601   0.01281   0.00669  -0.1461   0.3274   1.0000
   7.000   1.3749   0.01340   0.00716  -0.1439   0.2994   1.0000
   7.250   1.3897   0.01401   0.00766  -0.1416   0.2739   1.0000
   7.750   1.4185   0.01532   0.00874  -0.1372   0.2262   1.0000
   8.000   1.4320   0.01603   0.00933  -0.1349   0.2045   1.0000
   8.250   1.4465   0.01670   0.00994  -0.1328   0.1860   1.0000
   8.500   1.4609   0.01739   0.01056  -0.1308   0.1691   1.0000
   8.750   1.4747   0.01813   0.01123  -0.1286   0.1534   1.0000
   9.000   1.4885   0.01887   0.01193  -0.1266   0.1399   1.0000
   9.250   1.5018   0.01965   0.01268  -0.1245   0.1284   1.0000
   9.500   1.5143   0.02051   0.01348  -0.1224   0.1176   1.0000
   9.750   1.5284   0.02126   0.01424  -0.1205   0.1089   1.0000
  10.000   1.5414   0.02210   0.01508  -0.1185   0.1010   1.0000
  10.250   1.5528   0.02308   0.01603  -0.1164   0.0932   1.0000
  10.500   1.5663   0.02391   0.01691  -0.1147   0.0871   1.0000
  10.750   1.5757   0.02507   0.01804  -0.1124   0.0804   1.0000
  11.000   1.5895   0.02591   0.01895  -0.1108   0.0755   1.0000
  11.250   1.5987   0.02713   0.02016  -0.1088   0.0701   1.0000
  11.500   1.6109   0.02814   0.02124  -0.1071   0.0661   1.0000
  11.750   1.6213   0.02931   0.02243  -0.1053   0.0620   1.0000
  12.000   1.6281   0.03081   0.02395  -0.1032   0.0583   1.0000
  12.250   1.6401   0.03190   0.02513  -0.1017   0.0556   1.0000
  12.500   1.6489   0.03328   0.02655  -0.1001   0.0526   1.0000
  12.750   1.6522   0.03519   0.02849  -0.0980   0.0496   1.0000
  13.000   1.6638   0.03640   0.02980  -0.0967   0.0476   1.0000
  13.250   1.6721   0.03792   0.03139  -0.0952   0.0453   1.0000
  13.500   1.6765   0.03987   0.03337  -0.0936   0.0431   1.0000
  13.750   1.6794   0.04203   0.03562  -0.0920   0.0412   1.0000
  14.000   1.6878   0.04370   0.03740  -0.0909   0.0394   1.0000
  14.250   1.6935   0.04566   0.03944  -0.0897   0.0377   1.0000
  14.500   1.6947   0.04818   0.04201  -0.0884   0.0360   1.0000
  14.750   1.6927   0.05114   0.04507  -0.0872   0.0345   1.0000
  15.000   1.6988   0.05327   0.04732  -0.0864   0.0332   1.0000
  15.250   1.7026   0.05571   0.04986  -0.0857   0.0318   1.0000
  15.500   1.7038   0.05853   0.05276  -0.0851   0.0305   1.0000
  15.750   1.6979   0.06235   0.05665  -0.0845   0.0293   1.0000
  16.000   1.6966   0.06571   0.06013  -0.0842   0.0283   1.0000
  16.250   1.6987   0.06870   0.06326  -0.0841   0.0273   1.0000
  16.500   1.6987   0.07203   0.06670  -0.0841   0.0264   1.0000
  16.750   1.6975   0.07562   0.07039  -0.0844   0.0256   1.0000
  17.000   1.6932   0.07977   0.07462  -0.0849   0.0248   1.0000
  17.250   1.6837   0.08478   0.07973  -0.0857   0.0241   1.0000
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