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SG6043 (sg6043-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 200,000
Max Cl/Cd: 94.74 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6043-il-200000-n5.txt
Download as CSV file: xf-sg6043-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1259   0.09015   0.08642  -0.0818   0.9528   0.0278
  -7.750  -0.1137   0.08678   0.08305  -0.0850   0.9489   0.0287
  -7.500  -0.1082   0.08355   0.07984  -0.0876   0.9413   0.0298
  -7.250  -0.1032   0.07957   0.07588  -0.0929   0.9343   0.0304
  -7.000  -0.0947   0.07466   0.07098  -0.1001   0.9259   0.0306
  -6.750  -0.0780   0.07336   0.06969  -0.0965   0.9251   0.0320
  -6.250  -0.0495   0.05822   0.05445  -0.1159   0.9107   0.0215
  -6.000  -0.0220   0.05452   0.05069  -0.1217   0.9087   0.0210
  -5.750  -0.0095   0.05050   0.04661  -0.1254   0.8995   0.0205
  -5.500   0.0252   0.04328   0.03917  -0.1360   0.8961   0.0199
  -5.250   0.0685   0.03321   0.02853  -0.1483   0.8938   0.0192
  -5.000   0.0903   0.02767   0.02242  -0.1510   0.8860   0.0198
  -4.750   0.1285   0.02286   0.01675  -0.1556   0.8833   0.0208
  -4.500   0.1661   0.02019   0.01348  -0.1584   0.8812   0.0211
  -4.250   0.2034   0.01841   0.01126  -0.1607   0.8794   0.0214
  -4.000   0.2312   0.01745   0.01017  -0.1610   0.8748   0.0220
  -3.750   0.2600   0.01668   0.00929  -0.1613   0.8702   0.0227
  -3.500   0.2934   0.01591   0.00840  -0.1625   0.8670   0.0237
  -3.250   0.3288   0.01524   0.00757  -0.1641   0.8645   0.0256
  -3.000   0.3596   0.01473   0.00706  -0.1648   0.8605   0.0274
  -2.750   0.3866   0.01431   0.00660  -0.1647   0.8550   0.0289
  -2.500   0.4195   0.01383   0.00605  -0.1657   0.8511   0.0312
  -2.250   0.4549   0.01340   0.00557  -0.1672   0.8481   0.0357
  -2.000   0.4814   0.01314   0.00534  -0.1670   0.8422   0.0450
  -1.750   0.5113   0.01286   0.00509  -0.1674   0.8369   0.0640
  -1.500   0.5451   0.01259   0.00484  -0.1686   0.8330   0.0891
  -1.250   0.5731   0.01235   0.00477  -0.1688   0.8274   0.1306
  -1.000   0.6017   0.01208   0.00468  -0.1691   0.8215   0.1928
  -0.750   0.6348   0.01164   0.00458  -0.1705   0.8172   0.3184
  -0.500   0.6616   0.01125   0.00470  -0.1705   0.8112   0.4995
  -0.250   0.6879   0.01106   0.00475  -0.1700   0.8049   0.6111
   0.000   0.7177   0.01086   0.00471  -0.1700   0.8001   0.6943
   0.250   0.7369   0.01078   0.00480  -0.1679   0.7921   0.7644
   0.500   0.7584   0.01057   0.00471  -0.1659   0.7858   0.8553
   0.750   0.7833   0.01043   0.00462  -0.1649   0.7782   1.0000
   1.000   0.8127   0.01048   0.00457  -0.1651   0.7709   1.0000
   1.250   0.8399   0.01057   0.00459  -0.1650   0.7628   1.0000
   1.500   0.8686   0.01063   0.00456  -0.1650   0.7546   1.0000
   1.750   0.8946   0.01073   0.00461  -0.1646   0.7452   1.0000
   2.000   0.9240   0.01079   0.00459  -0.1647   0.7366   1.0000
   2.250   0.9485   0.01091   0.00467  -0.1640   0.7256   1.0000
   2.500   0.9745   0.01100   0.00472  -0.1635   0.7146   1.0000
   2.750   1.0010   0.01110   0.00477  -0.1631   0.7027   1.0000
   3.000   1.0270   0.01121   0.00481  -0.1626   0.6899   1.0000
   3.250   1.0516   0.01135   0.00490  -0.1618   0.6758   1.0000
   3.500   1.0763   0.01150   0.00499  -0.1611   0.6605   1.0000
   3.750   1.1005   0.01167   0.00511  -0.1602   0.6438   1.0000
   4.000   1.1239   0.01187   0.00524  -0.1592   0.6251   1.0000
   4.250   1.1464   0.01210   0.00540  -0.1581   0.6046   1.0000
   4.500   1.1682   0.01238   0.00559  -0.1568   0.5828   1.0000
   4.750   1.1888   0.01270   0.00580  -0.1553   0.5585   1.0000
   5.250   1.2261   0.01348   0.00633  -0.1516   0.5053   1.0000
   5.500   1.2431   0.01393   0.00667  -0.1495   0.4781   1.0000
   5.750   1.2587   0.01442   0.00704  -0.1472   0.4512   1.0000
   6.000   1.2726   0.01494   0.00744  -0.1446   0.4234   1.0000
   6.250   1.2861   0.01551   0.00789  -0.1420   0.3961   1.0000
   6.500   1.2988   0.01613   0.00839  -0.1393   0.3688   1.0000
   6.750   1.3109   0.01681   0.00895  -0.1366   0.3421   1.0000
   7.000   1.3239   0.01749   0.00953  -0.1341   0.3164   1.0000
   7.250   1.3359   0.01824   0.01017  -0.1315   0.2914   1.0000
   7.500   1.3476   0.01903   0.01085  -0.1290   0.2667   1.0000
   7.750   1.3597   0.01983   0.01158  -0.1266   0.2437   1.0000
   8.000   1.3716   0.02068   0.01234  -0.1242   0.2223   1.0000
   8.250   1.3832   0.02157   0.01315  -0.1219   0.2035   1.0000
   8.500   1.3957   0.02243   0.01396  -0.1198   0.1864   1.0000
   8.750   1.4081   0.02333   0.01484  -0.1177   0.1713   1.0000
   9.000   1.4201   0.02427   0.01575  -0.1157   0.1579   1.0000
   9.250   1.4320   0.02524   0.01670  -0.1136   0.1459   1.0000
   9.500   1.4444   0.02620   0.01768  -0.1118   0.1349   1.0000
   9.750   1.4562   0.02722   0.01872  -0.1099   0.1256   1.0000
  10.000   1.4667   0.02836   0.01986  -0.1079   0.1171   1.0000
  10.250   1.4786   0.02942   0.02096  -0.1061   0.1092   1.0000
  10.500   1.4888   0.03063   0.02220  -0.1043   0.1024   1.0000
  10.750   1.4995   0.03183   0.02346  -0.1026   0.0957   1.0000
  11.000   1.5088   0.03316   0.02483  -0.1008   0.0901   1.0000
  11.250   1.5189   0.03446   0.02620  -0.0991   0.0847   1.0000
  11.500   1.5259   0.03604   0.02780  -0.0973   0.0799   1.0000
  11.750   1.5364   0.03737   0.02926  -0.0959   0.0753   1.0000
  12.000   1.5438   0.03898   0.03093  -0.0943   0.0711   1.0000
  12.250   1.5506   0.04069   0.03271  -0.0927   0.0674   1.0000
  12.500   1.5590   0.04230   0.03443  -0.0914   0.0636   1.0000
  12.750   1.5646   0.04421   0.03640  -0.0900   0.0604   1.0000
  13.000   1.5697   0.04621   0.03848  -0.0886   0.0576   1.0000
  13.250   1.5767   0.04808   0.04049  -0.0875   0.0546   1.0000
  13.500   1.5813   0.05023   0.04273  -0.0863   0.0521   1.0000
  13.750   1.5829   0.05278   0.04533  -0.0853   0.0499   1.0000
  14.000   1.5884   0.05495   0.04766  -0.0844   0.0476   1.0000
  14.250   1.5924   0.05735   0.05019  -0.0836   0.0454   1.0000
  14.500   1.5944   0.06005   0.05298  -0.0829   0.0435   1.0000
  14.750   1.5932   0.06322   0.05623  -0.0824   0.0419   1.0000
  15.000   1.5958   0.06601   0.05918  -0.0820   0.0403   1.0000
  15.250   1.5974   0.06899   0.06232  -0.0817   0.0387   1.0000
  15.500   1.5975   0.07224   0.06571  -0.0816   0.0373   1.0000
  15.750   1.5956   0.07585   0.06943  -0.0818   0.0361   1.0000
  16.000   1.5911   0.07991   0.07358  -0.0821   0.0350   1.0000
  16.250   1.5899   0.08362   0.07745  -0.0825   0.0339   1.0000
  16.500   1.5883   0.08745   0.08146  -0.0831   0.0327   1.0000
  16.750   1.5855   0.09154   0.08572  -0.0839   0.0316   1.0000
  17.000   1.5816   0.09589   0.09020  -0.0851   0.0307   1.0000
  17.250   1.5766   0.10050   0.09494  -0.0864   0.0299   1.0000
  17.500   1.5701   0.10543   0.09996  -0.0881   0.0291   1.0000
  17.750   1.5649   0.11022   0.10490  -0.0897   0.0284   1.0000
  18.000   1.5603   0.11498   0.10985  -0.0915   0.0277   1.0000
  18.250   1.5550   0.11992   0.11497  -0.0936   0.0270   1.0000
  18.500   1.5494   0.12501   0.12021  -0.0959   0.0264   1.0000
  18.750   1.5435   0.13020   0.12555  -0.0984   0.0258   1.0000
  19.000   1.5377   0.13543   0.13092  -0.1012   0.0253   1.0000
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