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SG6043 (sg6043-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 200,000
Max Cl/Cd: 98.01 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6043-il-200000.txt
Download as CSV file: xf-sg6043-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.1974   0.09204   0.08868  -0.0635   0.9587   0.0413
  -6.750  -0.1929   0.08903   0.08569  -0.0693   0.9517   0.0432
  -6.500  -0.1808   0.08379   0.08044  -0.0844   0.9400   0.0439
  -6.250  -0.1694   0.08038   0.07706  -0.0795   0.9389   0.0447
  -6.000  -0.1475   0.07798   0.07465  -0.0792   0.9376   0.0474
  -5.750  -0.1444   0.07538   0.07207  -0.0803   0.9282   0.0487
  -5.500  -0.0998   0.06666   0.06301  -0.1073   0.9186   0.0526
  -5.250  -0.0941   0.06337   0.05989  -0.1034   0.9146   0.0535
  -5.000  -0.0745   0.06102   0.05755  -0.1031   0.9120   0.0548
  -4.750  -0.0418   0.05737   0.05384  -0.1084   0.9099   0.0576
  -4.500  -0.0053   0.05039   0.04637  -0.1212   0.9011   0.0638
  -4.250   0.0173   0.04770   0.04379  -0.1219   0.8981   0.0655
  -4.000   0.0715   0.04505   0.04054  -0.1305   0.8961   0.0752
  -3.750   0.1027   0.03977   0.03534  -0.1344   0.8949   0.0781
  -3.500   0.1156   0.03863   0.03423  -0.1329   0.8871   0.0817
  -3.250   0.1833   0.02948   0.02353  -0.1423   0.8865   0.0531
  -3.000   0.2272   0.02560   0.01894  -0.1454   0.8848   0.0439
  -2.750   0.2676   0.02333   0.01635  -0.1479   0.8831   0.0434
  -2.500   0.3091   0.02166   0.01438  -0.1504   0.8818   0.0444
  -2.250   0.3497   0.02054   0.01326  -0.1529   0.8804   0.0483
  -2.000   0.3922   0.01939   0.01199  -0.1553   0.8794   0.0513
  -1.750   0.4358   0.01823   0.01086  -0.1582   0.8786   0.0574
  -1.500   0.4493   0.01812   0.01079  -0.1555   0.8690   0.0669
  -1.250   0.4918   0.01717   0.00999  -0.1583   0.8673   0.1112
  -1.000   0.5354   0.01637   0.00947  -0.1615   0.8659   0.1850
  -0.750   0.5782   0.01485   0.00934  -0.1650   0.8648   0.6047
  -0.500   0.6123   0.01417   0.00904  -0.1652   0.8631   0.7653
  -0.250   0.6156   0.01418   0.00926  -0.1596   0.8529   0.8735
   0.000   0.6574   0.01371   0.00871  -0.1618   0.8504   1.0000
   0.250   0.7012   0.01340   0.00824  -0.1647   0.8482   1.0000
   0.500   0.7223   0.01359   0.00836  -0.1633   0.8395   1.0000
   0.750   0.7609   0.01336   0.00801  -0.1651   0.8354   1.0000
   1.000   0.8033   0.01305   0.00759  -0.1676   0.8323   1.0000
   1.250   0.8248   0.01321   0.00771  -0.1663   0.8231   1.0000
   1.500   0.8634   0.01296   0.00737  -0.1681   0.8182   1.0000
   1.750   0.8912   0.01297   0.00734  -0.1678   0.8103   1.0000
   2.000   0.9245   0.01283   0.00714  -0.1686   0.8034   1.0000
   2.250   0.9542   0.01279   0.00706  -0.1687   0.7954   1.0000
   2.500   0.9855   0.01268   0.00691  -0.1690   0.7871   1.0000
   2.750   1.0122   0.01268   0.00689  -0.1685   0.7773   1.0000
   3.000   1.0465   0.01252   0.00667  -0.1694   0.7691   1.0000
   3.250   1.0694   0.01258   0.00673  -0.1681   0.7575   1.0000
   3.500   1.0963   0.01257   0.00671  -0.1677   0.7465   1.0000
   3.750   1.1261   0.01250   0.00659  -0.1677   0.7355   1.0000
   4.000   1.1510   0.01250   0.00658  -0.1668   0.7222   1.0000
   4.250   1.1745   0.01255   0.00662  -0.1656   0.7079   1.0000
   4.500   1.1985   0.01259   0.00666  -0.1646   0.6926   1.0000
   4.750   1.2226   0.01265   0.00668  -0.1635   0.6758   1.0000
   5.000   1.2460   0.01276   0.00674  -0.1624   0.6579   1.0000
   5.250   1.2668   0.01293   0.00689  -0.1608   0.6379   1.0000
   5.500   1.2878   0.01314   0.00707  -0.1592   0.6169   1.0000
   5.750   1.3086   0.01339   0.00724  -0.1576   0.5945   1.0000
   6.000   1.3269   0.01370   0.00749  -0.1556   0.5697   1.0000
   6.250   1.3443   0.01408   0.00779  -0.1534   0.5432   1.0000
   6.500   1.3598   0.01453   0.00812  -0.1510   0.5147   1.0000
   6.750   1.3733   0.01505   0.00851  -0.1482   0.4847   1.0000
   7.000   1.3838   0.01563   0.00895  -0.1448   0.4535   1.0000
   7.250   1.3922   0.01629   0.00948  -0.1412   0.4212   1.0000
   7.500   1.3999   0.01704   0.01008  -0.1376   0.3888   1.0000
   7.750   1.4071   0.01787   0.01076  -0.1340   0.3568   1.0000
   8.000   1.4139   0.01878   0.01152  -0.1305   0.3262   1.0000
   8.250   1.4209   0.01975   0.01235  -0.1272   0.2968   1.0000
   8.500   1.4285   0.02076   0.01325  -0.1241   0.2693   1.0000
   8.750   1.4357   0.02185   0.01422  -0.1211   0.2446   1.0000
   9.000   1.4430   0.02299   0.01526  -0.1182   0.2222   1.0000
   9.250   1.4499   0.02422   0.01639  -0.1154   0.2033   1.0000
   9.500   1.4585   0.02541   0.01754  -0.1129   0.1856   1.0000
   9.750   1.4667   0.02667   0.01875  -0.1105   0.1707   1.0000
  10.000   1.4742   0.02802   0.02005  -0.1081   0.1580   1.0000
  10.250   1.4823   0.02937   0.02137  -0.1058   0.1466   1.0000
  10.500   1.4921   0.03066   0.02270  -0.1038   0.1361   1.0000
  10.750   1.4999   0.03214   0.02419  -0.1017   0.1272   1.0000
  11.000   1.5071   0.03369   0.02571  -0.0997   0.1192   1.0000
  11.250   1.5166   0.03512   0.02723  -0.0979   0.1117   1.0000
  11.500   1.5226   0.03690   0.02895  -0.0960   0.1052   1.0000
  11.750   1.5324   0.03834   0.03053  -0.0944   0.0990   1.0000
  12.000   1.5392   0.04009   0.03228  -0.0927   0.0937   1.0000
  12.250   1.5477   0.04181   0.03410  -0.0911   0.0887   1.0000
  12.500   1.5554   0.04350   0.03587  -0.0896   0.0841   1.0000
  12.750   1.5628   0.04553   0.03784  -0.0882   0.0797   1.0000
  13.000   1.5702   0.04727   0.03980  -0.0868   0.0760   1.0000
  13.250   1.5768   0.04917   0.04178  -0.0856   0.0724   1.0000
  13.500   1.5854   0.05128   0.04383  -0.0844   0.0687   1.0000
  13.750   1.5902   0.05336   0.04615  -0.0832   0.0659   1.0000
  14.000   1.5953   0.05552   0.04843  -0.0821   0.0629   1.0000
  14.250   1.6005   0.05777   0.05070  -0.0812   0.0603   1.0000
  14.500   1.6074   0.06016   0.05321  -0.0802   0.0576   1.0000
  14.750   1.6100   0.06275   0.05601  -0.0793   0.0553   1.0000
  15.000   1.6133   0.06531   0.05869  -0.0786   0.0531   1.0000
  15.250   1.6181   0.06778   0.06118  -0.0780   0.0511   1.0000
  15.500   1.6234   0.07062   0.06412  -0.0772   0.0490   1.0000
  15.750   1.6213   0.07396   0.06773  -0.0768   0.0474   1.0000
  16.000   1.6200   0.07731   0.07126  -0.0766   0.0458   1.0000
  16.250   1.6201   0.08049   0.07457  -0.0765   0.0444   1.0000
  16.500   1.6237   0.08334   0.07746  -0.0764   0.0430   1.0000
  16.750   1.6277   0.08670   0.08093  -0.0761   0.0416   1.0000
  17.000   1.6188   0.09130   0.08582  -0.0767   0.0409   1.0000
  17.250   1.6097   0.09613   0.09092  -0.0776   0.0402   1.0000
  17.500   1.5998   0.10122   0.09626  -0.0789   0.0395   1.0000
  17.750   1.5899   0.10644   0.10172  -0.0806   0.0388   1.0000
  18.000   1.5792   0.11189   0.10738  -0.0826   0.0382   1.0000
  18.250   1.5679   0.11761   0.11330  -0.0851   0.0376   1.0000
  18.500   1.5575   0.12326   0.11913  -0.0878   0.0370   1.0000
  18.750   1.5474   0.12900   0.12503  -0.0908   0.0365   1.0000
  19.000   1.5392   0.13444   0.13060  -0.0937   0.0360   1.0000
  19.250   1.5298   0.14028   0.13657  -0.0970   0.0356   1.0000
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