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S2046 (s2046-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 500,000
Max Cl/Cd: 101.89 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2046-il-500000.txt
Download as CSV file: xf-s2046-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2046                                           
  
 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  -0.3554   0.08643   0.08420  -0.0347   1.0000   0.0293
  -9.500  -0.3577   0.08158   0.07938  -0.0364   1.0000   0.0294
  -9.250  -0.3761   0.07343   0.07126  -0.0385   1.0000   0.0301
  -9.000  -0.3735   0.07050   0.06835  -0.0383   1.0000   0.0306
  -8.750  -0.3727   0.06739   0.06525  -0.0384   1.0000   0.0310
  -8.500  -0.3753   0.06374   0.06164  -0.0389   1.0000   0.0313
  -8.250  -0.3805   0.06002   0.05795  -0.0394   1.0000   0.0317
  -8.000  -0.3925   0.05591   0.05389  -0.0398   1.0000   0.0319
  -7.750  -0.4153   0.05269   0.05074  -0.0381   1.0000   0.0320
  -7.500  -0.5431   0.02389   0.01961  -0.0701   0.9955   0.0180
  -7.250  -0.5100   0.02071   0.01592  -0.0728   0.9936   0.0178
  -7.000  -0.4782   0.01858   0.01351  -0.0746   0.9909   0.0180
  -6.750  -0.4449   0.01701   0.01174  -0.0764   0.9883   0.0183
  -6.500  -0.4105   0.01581   0.01039  -0.0782   0.9861   0.0189
  -6.250  -0.3750   0.01478   0.00924  -0.0801   0.9843   0.0193
  -6.000  -0.3393   0.01386   0.00820  -0.0820   0.9826   0.0199
  -5.750  -0.3081   0.01312   0.00738  -0.0829   0.9784   0.0206
  -5.500  -0.2734   0.01253   0.00671  -0.0844   0.9755   0.0217
  -5.250  -0.2373   0.01191   0.00602  -0.0862   0.9733   0.0225
  -5.000  -0.2003   0.01093   0.00496  -0.0883   0.9715   0.0243
  -4.750  -0.1626   0.01044   0.00445  -0.0905   0.9701   0.0273
  -4.500  -0.1320   0.00996   0.00395  -0.0910   0.9647   0.0327
  -4.250  -0.0981   0.00945   0.00355  -0.0923   0.9608   0.0570
  -4.000  -0.0633   0.00921   0.00334  -0.0937   0.9576   0.0730
  -3.750  -0.0322   0.00897   0.00313  -0.0943   0.9524   0.0862
  -3.500  -0.0019   0.00872   0.00292  -0.0947   0.9460   0.1008
  -3.250   0.0294   0.00843   0.00268  -0.0953   0.9408   0.1197
  -3.000   0.0567   0.00816   0.00248  -0.0950   0.9315   0.1452
  -2.750   0.0846   0.00778   0.00228  -0.0950   0.9228   0.1959
  -2.500   0.1119   0.00728   0.00207  -0.0949   0.9138   0.2922
  -2.250   0.1385   0.00684   0.00198  -0.0947   0.9039   0.4044
  -2.000   0.1658   0.00664   0.00193  -0.0944   0.8949   0.4725
  -1.750   0.1930   0.00652   0.00189  -0.0940   0.8855   0.5178
  -1.500   0.2201   0.00645   0.00187  -0.0936   0.8754   0.5536
  -1.250   0.2475   0.00640   0.00185  -0.0933   0.8661   0.5822
  -1.000   0.2750   0.00636   0.00182  -0.0929   0.8564   0.6054
  -0.750   0.3023   0.00633   0.00180  -0.0925   0.8458   0.6252
  -0.500   0.3298   0.00631   0.00179  -0.0921   0.8356   0.6431
  -0.250   0.3573   0.00632   0.00177  -0.0918   0.8250   0.6604
   0.000   0.3847   0.00632   0.00177  -0.0914   0.8133   0.6768
   0.250   0.4118   0.00631   0.00179  -0.0910   0.8010   0.6970
   0.500   0.4388   0.00632   0.00183  -0.0905   0.7881   0.7200
   0.750   0.4657   0.00633   0.00186  -0.0900   0.7747   0.7403
   1.000   0.4926   0.00635   0.00188  -0.0895   0.7603   0.7574
   1.250   0.5195   0.00637   0.00190  -0.0891   0.7447   0.7730
   1.500   0.5462   0.00640   0.00193  -0.0886   0.7278   0.7887
   1.750   0.5725   0.00645   0.00196  -0.0880   0.7090   0.8053
   2.000   0.5986   0.00648   0.00200  -0.0874   0.6871   0.8240
   2.250   0.6237   0.00653   0.00204  -0.0866   0.6616   0.8454
   2.500   0.6472   0.00658   0.00208  -0.0854   0.6293   0.8759
   2.750   0.6725   0.00660   0.00207  -0.0845   0.5839   1.0000
   3.000   0.6982   0.00696   0.00217  -0.0841   0.5344   1.0000
   3.250   0.7237   0.00734   0.00233  -0.0837   0.4868   1.0000
   3.500   0.7493   0.00772   0.00251  -0.0834   0.4449   1.0000
   3.750   0.7754   0.00805   0.00269  -0.0831   0.4110   1.0000
   4.000   0.8013   0.00840   0.00290  -0.0828   0.3775   1.0000
   4.250   0.8272   0.00875   0.00312  -0.0824   0.3466   1.0000
   4.500   0.8531   0.00910   0.00334  -0.0821   0.3173   1.0000
   4.750   0.8788   0.00946   0.00358  -0.0818   0.2888   1.0000
   5.000   0.9046   0.00982   0.00382  -0.0815   0.2619   1.0000
   5.250   0.9299   0.01022   0.00411  -0.0811   0.2324   1.0000
   5.500   0.9545   0.01071   0.00442  -0.0807   0.1968   1.0000
   5.750   0.9784   0.01130   0.00480  -0.0801   0.1560   1.0000
   6.000   1.0019   0.01195   0.00524  -0.0795   0.1188   1.0000
   6.250   1.0255   0.01257   0.00573  -0.0789   0.0939   1.0000
   6.500   1.0494   0.01315   0.00623  -0.0784   0.0789   1.0000
   6.750   1.0736   0.01367   0.00673  -0.0778   0.0693   1.0000
   7.000   1.0965   0.01435   0.00736  -0.0770   0.0614   1.0000
   7.250   1.1213   0.01475   0.00783  -0.0765   0.0574   1.0000
   7.500   1.1444   0.01537   0.00843  -0.0758   0.0526   1.0000
   7.750   1.1667   0.01605   0.00917  -0.0749   0.0490   1.0000
   8.000   1.1905   0.01653   0.00971  -0.0743   0.0464   1.0000
   8.250   1.2134   0.01708   0.01029  -0.0736   0.0438   1.0000
   8.500   1.2329   0.01805   0.01129  -0.0724   0.0405   1.0000
   8.750   1.2548   0.01868   0.01200  -0.0715   0.0386   1.0000
   9.000   1.2782   0.01909   0.01246  -0.0709   0.0364   1.0000
   9.250   1.3007   0.01957   0.01298  -0.0702   0.0342   1.0000
   9.500   1.3196   0.02044   0.01387  -0.0690   0.0320   1.0000
   9.750   1.3357   0.02164   0.01517  -0.0674   0.0302   1.0000
  10.000   1.3574   0.02213   0.01576  -0.0665   0.0289   1.0000
  10.250   1.3780   0.02266   0.01636  -0.0656   0.0271   1.0000
  10.500   1.3980   0.02321   0.01694  -0.0646   0.0254   1.0000
  10.750   1.4064   0.02496   0.01875  -0.0622   0.0232   1.0000
  11.000   1.4266   0.02537   0.01926  -0.0612   0.0222   1.0000
  11.250   1.4430   0.02603   0.02001  -0.0597   0.0208   1.0000
  11.500   1.4570   0.02669   0.02075  -0.0579   0.0195   1.0000
  11.750   1.4657   0.02772   0.02181  -0.0554   0.0184   1.0000
  12.000   1.4638   0.02971   0.02392  -0.0520   0.0172   1.0000
  12.250   1.4742   0.03070   0.02505  -0.0501   0.0165   1.0000
  12.500   1.4819   0.03195   0.02641  -0.0481   0.0157   1.0000
  12.750   1.4895   0.03321   0.02777  -0.0464   0.0149   1.0000
  13.000   1.4956   0.03464   0.02927  -0.0447   0.0142   1.0000
  13.250   1.4978   0.03652   0.03122  -0.0431   0.0136   1.0000
  13.500   1.4891   0.03967   0.03451  -0.0413   0.0131   1.0000
  13.750   1.4863   0.04244   0.03745  -0.0402   0.0127   1.0000
  14.000   1.4874   0.04489   0.04005  -0.0395   0.0124   1.0000
  14.250   1.4849   0.04792   0.04325  -0.0392   0.0121   1.0000
  14.500   1.4810   0.05130   0.04680  -0.0392   0.0118   1.0000
  14.750   1.4753   0.05513   0.05079  -0.0398   0.0116   1.0000
  15.000   1.4685   0.05935   0.05517  -0.0408   0.0114   1.0000
  15.250   1.4602   0.06404   0.06001  -0.0424   0.0111   1.0000
  15.500   1.4496   0.06940   0.06553  -0.0446   0.0110   1.0000
  15.750   1.4382   0.07525   0.07154  -0.0473   0.0109   1.0000
  16.000   1.4252   0.08171   0.07816  -0.0506   0.0108   1.0000
  16.250   1.4104   0.08886   0.08547  -0.0545   0.0107   1.0000
  16.500   1.3945   0.09652   0.09329  -0.0588   0.0107   1.0000
  16.750   1.3763   0.10492   0.10186  -0.0636   0.0106   1.0000
  17.000   1.3572   0.11380   0.11091  -0.0689   0.0106   1.0000
  17.250   1.3352   0.12361   0.12090  -0.0749   0.0106   1.0000
  17.500   1.3106   0.13451   0.13198  -0.0817   0.0107   1.0000
  17.750   1.2806   0.14727   0.14495  -0.0898   0.0109   1.0000
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