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SG6043 (sg6043-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.24 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6043-il-1000000-n5.txt
Download as CSV file: xf-sg6043-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1085   0.08890   0.08701  -0.0968   0.9673   0.0064
  -9.250  -0.1027   0.08375   0.08187  -0.1004   0.9640   0.0067
  -8.250  -0.1252   0.02065   0.01760  -0.1748   0.9002   0.0081
  -8.000  -0.1022   0.01794   0.01445  -0.1766   0.8918   0.0084
  -7.750  -0.0779   0.01649   0.01273  -0.1772   0.8841   0.0086
  -7.500  -0.0518   0.01541   0.01140  -0.1778   0.8774   0.0088
  -7.250  -0.0271   0.01419   0.00993  -0.1781   0.8704   0.0090
  -7.000  -0.0012   0.01315   0.00868  -0.1784   0.8640   0.0092
  -6.750   0.0251   0.01250   0.00790  -0.1785   0.8580   0.0093
  -6.500   0.0518   0.01202   0.00732  -0.1786   0.8516   0.0095
  -6.250   0.0789   0.01154   0.00673  -0.1786   0.8460   0.0097
  -6.000   0.1058   0.01108   0.00617  -0.1787   0.8403   0.0098
  -5.750   0.1329   0.01067   0.00565  -0.1787   0.8346   0.0101
  -5.500   0.1602   0.01027   0.00515  -0.1787   0.8297   0.0103
  -5.250   0.1875   0.00988   0.00469  -0.1787   0.8245   0.0105
  -5.000   0.2149   0.00956   0.00428  -0.1787   0.8193   0.0107
  -4.750   0.2425   0.00929   0.00393  -0.1787   0.8145   0.0110
  -4.500   0.2702   0.00906   0.00365  -0.1786   0.8096   0.0113
  -4.250   0.2978   0.00885   0.00338  -0.1786   0.8043   0.0115
  -4.000   0.3254   0.00847   0.00293  -0.1786   0.7993   0.0119
  -3.750   0.3532   0.00822   0.00265  -0.1787   0.7939   0.0122
  -3.500   0.3808   0.00804   0.00243  -0.1786   0.7883   0.0127
  -3.250   0.4085   0.00790   0.00224  -0.1786   0.7832   0.0131
  -3.000   0.4364   0.00775   0.00207  -0.1786   0.7782   0.0135
  -2.750   0.4642   0.00764   0.00192  -0.1785   0.7728   0.0139
  -2.500   0.4918   0.00755   0.00179  -0.1784   0.7677   0.0144
  -2.250   0.5198   0.00742   0.00165  -0.1784   0.7622   0.0152
  -2.000   0.5472   0.00735   0.00155  -0.1783   0.7559   0.0167
  -1.750   0.5748   0.00728   0.00146  -0.1781   0.7498   0.0191
  -1.500   0.6024   0.00716   0.00139  -0.1781   0.7427   0.0328
  -1.250   0.6295   0.00711   0.00135  -0.1779   0.7357   0.0476
  -1.000   0.6570   0.00705   0.00132  -0.1778   0.7281   0.0613
  -0.750   0.6838   0.00702   0.00130  -0.1776   0.7197   0.0783
  -0.500   0.7108   0.00697   0.00129  -0.1774   0.7100   0.1034
  -0.250   0.7376   0.00690   0.00130  -0.1772   0.7001   0.1437
   0.000   0.7639   0.00685   0.00132  -0.1769   0.6890   0.1942
   0.250   0.7908   0.00671   0.00136  -0.1768   0.6773   0.2882
   0.500   0.8172   0.00659   0.00142  -0.1767   0.6643   0.3898
   0.750   0.8431   0.00650   0.00152  -0.1764   0.6492   0.4983
   1.000   0.8685   0.00653   0.00161  -0.1759   0.6335   0.5593
   1.250   0.8936   0.00660   0.00170  -0.1753   0.6172   0.6004
   1.500   0.9183   0.00669   0.00181  -0.1747   0.5995   0.6426
   1.750   0.9423   0.00678   0.00194  -0.1739   0.5802   0.7010
   2.000   0.9659   0.00686   0.00209  -0.1730   0.5587   0.7646
   2.250   0.9875   0.00695   0.00226  -0.1716   0.5358   0.8396
   2.500   1.0036   0.00691   0.00235  -0.1689   0.5151   1.0000
   2.750   1.0270   0.00718   0.00250  -0.1680   0.4904   1.0000
   3.000   1.0493   0.00750   0.00267  -0.1669   0.4616   1.0000
   3.250   1.0711   0.00786   0.00286  -0.1658   0.4306   1.0000
   3.500   1.0931   0.00821   0.00306  -0.1647   0.4025   1.0000
   3.750   1.1153   0.00854   0.00327  -0.1636   0.3766   1.0000
   4.000   1.1376   0.00886   0.00347  -0.1626   0.3543   1.0000
   4.250   1.1591   0.00922   0.00370  -0.1614   0.3290   1.0000
   4.500   1.1804   0.00958   0.00394  -0.1602   0.3048   1.0000
   4.750   1.2018   0.00991   0.00417  -0.1590   0.2853   1.0000
   5.000   1.2217   0.01028   0.00443  -0.1575   0.2643   1.0000
   5.250   1.2415   0.01065   0.00469  -0.1561   0.2429   1.0000
   5.500   1.2606   0.01104   0.00498  -0.1544   0.2220   1.0000
   5.750   1.2785   0.01150   0.00531  -0.1526   0.1981   1.0000
   6.000   1.2970   0.01193   0.00564  -0.1510   0.1784   1.0000
   6.250   1.3165   0.01231   0.00594  -0.1495   0.1643   1.0000
   6.500   1.3359   0.01268   0.00626  -0.1480   0.1523   1.0000
   6.750   1.3549   0.01307   0.00660  -0.1465   0.1403   1.0000
   7.000   1.3735   0.01349   0.00696  -0.1449   0.1285   1.0000
   7.500   1.4112   0.01429   0.00769  -0.1418   0.1102   1.0000
   7.750   1.4294   0.01473   0.00809  -0.1402   0.1022   1.0000
   8.000   1.4473   0.01518   0.00851  -0.1386   0.0942   1.0000
   8.250   1.4657   0.01560   0.00892  -0.1371   0.0882   1.0000
   8.500   1.4829   0.01609   0.00939  -0.1354   0.0821   1.0000
   8.750   1.5009   0.01653   0.00983  -0.1339   0.0772   1.0000
   9.000   1.5175   0.01707   0.01035  -0.1322   0.0713   1.0000
   9.250   1.5344   0.01758   0.01086  -0.1305   0.0666   1.0000
   9.500   1.5506   0.01815   0.01142  -0.1288   0.0617   1.0000
   9.750   1.5663   0.01873   0.01201  -0.1271   0.0572   1.0000
  10.000   1.5814   0.01938   0.01265  -0.1253   0.0523   1.0000
  10.250   1.5963   0.02004   0.01331  -0.1235   0.0483   1.0000
  10.500   1.6111   0.02072   0.01400  -0.1217   0.0449   1.0000
  10.750   1.6249   0.02148   0.01476  -0.1199   0.0417   1.0000
  11.000   1.6398   0.02216   0.01548  -0.1182   0.0395   1.0000
  11.250   1.6531   0.02297   0.01631  -0.1165   0.0369   1.0000
  11.500   1.6661   0.02383   0.01718  -0.1147   0.0348   1.0000
  11.750   1.6800   0.02462   0.01802  -0.1131   0.0334   1.0000
  12.000   1.6931   0.02549   0.01893  -0.1114   0.0318   1.0000
  12.250   1.7047   0.02649   0.01996  -0.1096   0.0301   1.0000
  12.500   1.7164   0.02751   0.02102  -0.1079   0.0286   1.0000
  12.750   1.7286   0.02850   0.02206  -0.1064   0.0274   1.0000
  13.000   1.7397   0.02959   0.02320  -0.1048   0.0259   1.0000
  13.250   1.7493   0.03083   0.02448  -0.1031   0.0244   1.0000
  13.500   1.7592   0.03208   0.02577  -0.1015   0.0230   1.0000
  13.750   1.7689   0.03338   0.02712  -0.1000   0.0216   1.0000
  14.000   1.7767   0.03487   0.02864  -0.0984   0.0199   1.0000
  14.250   1.7849   0.03635   0.03018  -0.0969   0.0188   1.0000
  14.500   1.7929   0.03790   0.03179  -0.0955   0.0176   1.0000
  14.750   1.7992   0.03964   0.03358  -0.0941   0.0165   1.0000
  15.000   1.8055   0.04144   0.03544  -0.0928   0.0156   1.0000
  15.250   1.8122   0.04324   0.03731  -0.0916   0.0150   1.0000
  15.500   1.8178   0.04519   0.03933  -0.0905   0.0143   1.0000
  15.750   1.8219   0.04735   0.04156  -0.0894   0.0135   1.0000
  16.000   1.8250   0.04970   0.04397  -0.0884   0.0128   1.0000
  16.250   1.8291   0.05198   0.04635  -0.0875   0.0124   1.0000
  16.500   1.8326   0.05441   0.04886  -0.0868   0.0118   1.0000
  16.750   1.8346   0.05706   0.05159  -0.0862   0.0113   1.0000
  17.000   1.8351   0.05998   0.05458  -0.0857   0.0107   1.0000
  17.250   1.8346   0.06311   0.05780  -0.0854   0.0102   1.0000
  17.500   1.8348   0.06626   0.06104  -0.0852   0.0099   1.0000
  17.750   1.8346   0.06952   0.06441  -0.0852   0.0097   1.0000
  18.000   1.8334   0.07301   0.06800  -0.0853   0.0094   1.0000
  18.250   1.8310   0.07674   0.07184  -0.0857   0.0092   1.0000
  18.500   1.8275   0.08074   0.07595  -0.0863   0.0089   1.0000
  18.750   1.8227   0.08505   0.08036  -0.0871   0.0087   1.0000
  19.000   1.8167   0.08964   0.08506  -0.0881   0.0084   1.0000
  19.250   1.8093   0.09454   0.09007  -0.0894   0.0082   1.0000
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