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SG6041 (sg6041-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SG6041 (sg6041-il)
Reynolds number: 100,000
Max Cl/Cd: 53.46 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6041-il-100000.txt
Download as CSV file: xf-sg6041-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6041                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4237   0.10357   0.09848  -0.0331   1.0000   0.0927
  -9.250  -0.4211   0.10054   0.09549  -0.0331   1.0000   0.0959
  -9.000  -0.4274   0.09747   0.09250  -0.0346   1.0000   0.0997
  -8.750  -0.4501   0.09472   0.08988  -0.0385   1.0000   0.1018
  -8.500  -0.4794   0.09192   0.08723  -0.0414   1.0000   0.1023
  -8.250  -0.5061   0.08949   0.08486  -0.0419   1.0000   0.1025
  -8.000  -0.4503   0.08476   0.08011  -0.0350   1.0000   0.1083
  -7.750  -0.4638   0.08220   0.07766  -0.0341   1.0000   0.1106
  -7.500  -0.4849   0.07939   0.07493  -0.0339   1.0000   0.1128
  -7.250  -0.5127   0.07668   0.07222  -0.0346   1.0000   0.1157
  -7.000  -0.5508   0.07509   0.07033  -0.0350   1.0000   0.1175
  -6.750  -0.5266   0.07009   0.06566  -0.0314   1.0000   0.1206
  -6.500  -0.5255   0.06759   0.06318  -0.0293   1.0000   0.1245
  -6.250  -0.5443   0.06450   0.05975  -0.0302   1.0000   0.1330
  -6.000  -0.5333   0.06121   0.05665  -0.0274   1.0000   0.1365
  -5.250  -0.5211   0.05255   0.04769  -0.0242   1.0000   0.1651
  -5.000  -0.5130   0.04995   0.04498  -0.0231   1.0000   0.1795
  -4.750  -0.4761   0.03718   0.03037  -0.0247   1.0000   0.0698
  -4.500  -0.4537   0.03390   0.02600  -0.0227   1.0000   0.0615
  -4.250  -0.4330   0.03131   0.02305  -0.0217   1.0000   0.0616
  -4.000  -0.4107   0.02851   0.01986  -0.0208   1.0000   0.0622
  -3.750  -0.3874   0.02630   0.01737  -0.0198   1.0000   0.0630
  -3.500  -0.3646   0.02465   0.01557  -0.0189   1.0000   0.0655
  -3.250  -0.3422   0.02366   0.01441  -0.0178   1.0000   0.0720
  -3.000  -0.3193   0.02217   0.01285  -0.0168   1.0000   0.0786
  -2.750  -0.2971   0.02119   0.01181  -0.0157   1.0000   0.0903
  -2.500  -0.2758   0.02012   0.01090  -0.0147   1.0000   0.1085
  -2.250  -0.2550   0.01920   0.01016  -0.0136   1.0000   0.1392
  -2.000  -0.2347   0.01818   0.00955  -0.0126   1.0000   0.2005
  -1.750  -0.2316   0.01582   0.00997  -0.0064   1.0000   0.7810
  -1.500  -0.1930   0.01599   0.01031  -0.0059   1.0000   0.9560
  -1.250  -0.1481   0.01622   0.01022  -0.0102   1.0000   1.0000
  -1.000  -0.1313   0.01633   0.01011  -0.0094   0.9993   1.0000
  -0.750  -0.0862   0.01689   0.01040  -0.0138   0.9909   1.0000
  -0.500  -0.0415   0.01749   0.01077  -0.0181   0.9828   1.0000
  -0.250   0.0005   0.01794   0.01103  -0.0217   0.9733   1.0000
   0.000   0.0395   0.01832   0.01126  -0.0246   0.9633   1.0000
   0.250   0.0818   0.01874   0.01156  -0.0281   0.9538   1.0000
   0.500   0.1265   0.01912   0.01182  -0.0318   0.9443   1.0000
   0.750   0.1635   0.01936   0.01198  -0.0341   0.9326   1.0000
   1.000   0.2029   0.01958   0.01215  -0.0366   0.9213   1.0000
   1.250   0.2484   0.01976   0.01229  -0.0401   0.9113   1.0000
   1.500   0.2937   0.01981   0.01232  -0.0434   0.9004   1.0000
   1.750   0.3321   0.01980   0.01231  -0.0453   0.8875   1.0000
   2.000   0.3730   0.01969   0.01222  -0.0474   0.8749   1.0000
   2.250   0.4181   0.01943   0.01201  -0.0501   0.8628   1.0000
   2.500   0.4822   0.01869   0.01136  -0.0558   0.8550   1.0000
   2.750   0.5230   0.01816   0.01089  -0.0572   0.8411   1.0000
   3.000   0.5628   0.01755   0.01038  -0.0582   0.8266   1.0000
   3.250   0.6014   0.01690   0.00980  -0.0589   0.8113   1.0000
   3.500   0.6326   0.01636   0.00932  -0.0582   0.7922   1.0000
   3.750   0.6632   0.01582   0.00886  -0.0574   0.7704   1.0000
   4.000   0.6927   0.01533   0.00841  -0.0564   0.7455   1.0000
   4.250   0.7210   0.01494   0.00802  -0.0552   0.7153   1.0000
   4.500   0.7489   0.01467   0.00772  -0.0540   0.6788   1.0000
   4.750   0.7731   0.01464   0.00757  -0.0523   0.6331   1.0000
   5.000   0.7939   0.01485   0.00758  -0.0502   0.5788   1.0000
   5.250   0.8122   0.01529   0.00771  -0.0478   0.5182   1.0000
   5.500   0.8282   0.01595   0.00803  -0.0453   0.4568   1.0000
   5.750   0.8431   0.01676   0.00849  -0.0428   0.3987   1.0000
   6.000   0.8583   0.01767   0.00907  -0.0406   0.3483   1.0000
   6.250   0.8743   0.01865   0.00972  -0.0386   0.3066   1.0000
   6.500   0.8917   0.01961   0.01052  -0.0369   0.2712   1.0000
   6.750   0.9104   0.02063   0.01135  -0.0354   0.2431   1.0000
   7.000   0.9299   0.02169   0.01221  -0.0342   0.2196   1.0000
   7.250   0.9505   0.02273   0.01323  -0.0331   0.1993   1.0000
   7.500   0.9720   0.02384   0.01432  -0.0322   0.1824   1.0000
   7.750   0.9935   0.02497   0.01543  -0.0313   0.1675   1.0000
   8.000   1.0159   0.02623   0.01670  -0.0306   0.1547   1.0000
   8.250   1.0383   0.02754   0.01801  -0.0299   0.1433   1.0000
   8.500   1.0620   0.02900   0.01939  -0.0295   0.1329   1.0000
   8.750   1.0807   0.03011   0.02074  -0.0281   0.1234   1.0000
   9.000   1.1019   0.03182   0.02259  -0.0273   0.1150   1.0000
   9.250   1.1241   0.03341   0.02412  -0.0268   0.1072   1.0000
   9.500   1.1395   0.03517   0.02628  -0.0250   0.1004   1.0000
   9.750   1.1599   0.03700   0.02818  -0.0242   0.0947   1.0000
  10.000   1.1730   0.03963   0.03120  -0.0224   0.0903   1.0000
  10.250   1.1844   0.04160   0.03350  -0.0203   0.0855   1.0000
  10.500   1.2021   0.04372   0.03562  -0.0195   0.0814   1.0000
  10.750   1.2065   0.04732   0.03963  -0.0171   0.0793   1.0000
  11.000   1.2018   0.05039   0.04324  -0.0134   0.0778   1.0000
  11.250   1.1935   0.05362   0.04691  -0.0098   0.0763   1.0000
  11.500   1.1813   0.05684   0.05049  -0.0062   0.0751   1.0000
  11.750   1.1638   0.06003   0.05397  -0.0023   0.0744   1.0000
  12.000   1.1426   0.06354   0.05773   0.0009   0.0739   1.0000
  12.250   1.1141   0.06801   0.06247   0.0032   0.0743   1.0000
  12.500   1.0815   0.07335   0.06804   0.0038   0.0750   1.0000
  12.750   1.0454   0.08013   0.07502   0.0023   0.0764   1.0000
  13.000   1.0123   0.08787   0.08287  -0.0011   0.0778   1.0000
  13.250   0.9838   0.09646   0.09153  -0.0055   0.0791   1.0000
  13.500   0.9598   0.10562   0.10072  -0.0103   0.0799   1.0000
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