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S2046 (s2046-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 500,000
Max Cl/Cd: 84.84 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2046-il-500000-n5.txt
Download as CSV file: xf-s2046-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4814   0.10070   0.09821  -0.0253   1.0000   0.0101
 -10.500  -0.6766   0.04981   0.04714  -0.0555   1.0000   0.0092
 -10.250  -0.7089   0.04088   0.03803  -0.0645   1.0000   0.0091
 -10.000  -0.7164   0.03604   0.03290  -0.0686   1.0000   0.0091
  -9.750  -0.7139   0.03282   0.02941  -0.0695   1.0000   0.0092
  -9.500  -0.7125   0.02893   0.02513  -0.0699   1.0000   0.0093
  -9.250  -0.6949   0.02549   0.02130  -0.0719   0.9983   0.0095
  -9.000  -0.6664   0.02304   0.01856  -0.0746   0.9954   0.0097
  -8.750  -0.6369   0.02131   0.01662  -0.0766   0.9927   0.0099
  -8.500  -0.6073   0.01995   0.01507  -0.0782   0.9896   0.0101
  -8.250  -0.5765   0.01876   0.01372  -0.0797   0.9867   0.0104
  -8.000  -0.5446   0.01766   0.01246  -0.0814   0.9845   0.0107
  -7.750  -0.5126   0.01666   0.01132  -0.0829   0.9822   0.0110
  -7.500  -0.4832   0.01579   0.01031  -0.0837   0.9781   0.0113
  -7.250  -0.4520   0.01495   0.00934  -0.0849   0.9747   0.0116
  -7.000  -0.4199   0.01420   0.00848  -0.0861   0.9718   0.0119
  -6.750  -0.3884   0.01352   0.00770  -0.0872   0.9684   0.0122
  -6.500  -0.3592   0.01296   0.00706  -0.0877   0.9629   0.0125
  -6.250  -0.3278   0.01238   0.00640  -0.0886   0.9587   0.0129
  -6.000  -0.2967   0.01170   0.00566  -0.0896   0.9544   0.0138
  -5.750  -0.2678   0.01124   0.00514  -0.0899   0.9480   0.0144
  -5.500  -0.2371   0.01082   0.00466  -0.0905   0.9428   0.0151
  -5.250  -0.2080   0.01046   0.00425  -0.0908   0.9364   0.0160
  -5.000  -0.1787   0.01015   0.00386  -0.0910   0.9299   0.0168
  -4.750  -0.1498   0.00981   0.00348  -0.0912   0.9234   0.0188
  -4.500  -0.1213   0.00952   0.00317  -0.0913   0.9164   0.0225
  -4.250  -0.0930   0.00920   0.00290  -0.0913   0.9097   0.0349
  -4.000  -0.0650   0.00897   0.00269  -0.0913   0.9023   0.0478
  -3.750  -0.0370   0.00878   0.00251  -0.0913   0.8950   0.0585
  -3.500  -0.0091   0.00860   0.00235  -0.0912   0.8867   0.0699
  -3.250   0.0187   0.00844   0.00219  -0.0911   0.8779   0.0809
  -3.000   0.0463   0.00829   0.00204  -0.0909   0.8676   0.0937
  -2.750   0.0738   0.00813   0.00190  -0.0907   0.8553   0.1132
  -2.500   0.1013   0.00794   0.00175  -0.0906   0.8423   0.1383
  -2.250   0.1289   0.00777   0.00163  -0.0904   0.8298   0.1664
  -2.000   0.1567   0.00760   0.00151  -0.0903   0.8179   0.2019
  -1.750   0.1844   0.00737   0.00141  -0.0903   0.8061   0.2551
  -1.500   0.2120   0.00707   0.00132  -0.0904   0.7942   0.3387
  -1.000   0.2674   0.00674   0.00128  -0.0902   0.7698   0.4694
  -0.750   0.2952   0.00669   0.00127  -0.0901   0.7569   0.5041
  -0.500   0.3229   0.00668   0.00127  -0.0899   0.7436   0.5300
  -0.250   0.3505   0.00668   0.00128  -0.0897   0.7290   0.5530
   0.000   0.3781   0.00671   0.00129  -0.0894   0.7136   0.5726
   0.250   0.4054   0.00673   0.00132  -0.0891   0.6967   0.5987
   0.500   0.4325   0.00676   0.00137  -0.0888   0.6779   0.6292
   0.750   0.4596   0.00681   0.00143  -0.0885   0.6573   0.6538
   1.000   0.4864   0.00691   0.00148  -0.0881   0.6343   0.6719
   1.250   0.5132   0.00702   0.00153  -0.0877   0.6080   0.6855
   1.500   0.5397   0.00717   0.00161  -0.0873   0.5791   0.6981
   1.750   0.5660   0.00736   0.00169  -0.0869   0.5464   0.7107
   2.000   0.5921   0.00758   0.00180  -0.0865   0.5113   0.7237
   2.250   0.6178   0.00783   0.00194  -0.0860   0.4745   0.7369
   2.500   0.6434   0.00810   0.00208  -0.0856   0.4357   0.7506
   2.750   0.6685   0.00843   0.00225  -0.0850   0.3920   0.7650
   3.000   0.6938   0.00873   0.00243  -0.0846   0.3558   0.7803
   3.500   0.7448   0.00920   0.00278  -0.0836   0.3003   0.8154
   3.750   0.7700   0.00937   0.00295  -0.0830   0.2801   0.8384
   4.000   0.7934   0.00952   0.00312  -0.0820   0.2569   0.8744
   4.250   0.8196   0.00966   0.00328  -0.0816   0.2309   1.0000
   4.500   0.8456   0.01003   0.00352  -0.0814   0.2034   1.0000
   4.750   0.8711   0.01044   0.00378  -0.0810   0.1739   1.0000
   5.000   0.8965   0.01085   0.00406  -0.0807   0.1474   1.0000
   5.250   0.9216   0.01129   0.00439  -0.0803   0.1228   1.0000
   5.750   0.9717   0.01219   0.00509  -0.0795   0.0841   1.0000
   6.000   0.9969   0.01260   0.00544  -0.0791   0.0728   1.0000
   6.250   1.0222   0.01299   0.00581  -0.0787   0.0646   1.0000
   6.500   1.0475   0.01336   0.00617  -0.0783   0.0584   1.0000
   6.750   1.0723   0.01378   0.00657  -0.0779   0.0522   1.0000
   7.000   1.0973   0.01416   0.00697  -0.0775   0.0481   1.0000
   7.250   1.1221   0.01456   0.00740  -0.0770   0.0447   1.0000
   7.500   1.1462   0.01504   0.00787  -0.0764   0.0410   1.0000
   7.750   1.1704   0.01547   0.00834  -0.0759   0.0386   1.0000
   8.000   1.1946   0.01588   0.00880  -0.0753   0.0364   1.0000
   8.250   1.2183   0.01635   0.00930  -0.0747   0.0342   1.0000
   8.500   1.2411   0.01691   0.00988  -0.0740   0.0319   1.0000
   8.750   1.2639   0.01744   0.01045  -0.0733   0.0299   1.0000
   9.000   1.2873   0.01786   0.01094  -0.0727   0.0281   1.0000
   9.250   1.3099   0.01836   0.01146  -0.0720   0.0260   1.0000
   9.500   1.3314   0.01897   0.01209  -0.0712   0.0242   1.0000
   9.750   1.3523   0.01962   0.01281  -0.0702   0.0229   1.0000
  10.000   1.3738   0.02015   0.01343  -0.0694   0.0218   1.0000
  10.250   1.3947   0.02072   0.01406  -0.0685   0.0204   1.0000
  10.500   1.4149   0.02133   0.01471  -0.0675   0.0190   1.0000
  10.750   1.4330   0.02212   0.01553  -0.0663   0.0174   1.0000
  11.000   1.4521   0.02274   0.01624  -0.0651   0.0165   1.0000
  11.250   1.4701   0.02343   0.01701  -0.0639   0.0153   1.0000
  11.500   1.4868   0.02419   0.01784  -0.0625   0.0142   1.0000
  11.750   1.5007   0.02506   0.01876  -0.0607   0.0132   1.0000
  12.000   1.5124   0.02592   0.01971  -0.0585   0.0124   1.0000
  12.250   1.5229   0.02682   0.02071  -0.0563   0.0117   1.0000
  12.500   1.5323   0.02780   0.02179  -0.0541   0.0110   1.0000
  12.750   1.5405   0.02891   0.02298  -0.0519   0.0103   1.0000
  13.000   1.5464   0.03024   0.02438  -0.0497   0.0097   1.0000
  13.250   1.5513   0.03170   0.02595  -0.0476   0.0093   1.0000
  13.500   1.5564   0.03322   0.02761  -0.0458   0.0089   1.0000
  13.750   1.5607   0.03487   0.02939  -0.0441   0.0085   1.0000
  14.000   1.5639   0.03673   0.03136  -0.0427   0.0081   1.0000
  14.250   1.5654   0.03883   0.03359  -0.0415   0.0078   1.0000
  14.500   1.5656   0.04121   0.03609  -0.0405   0.0075   1.0000
  14.750   1.5638   0.04395   0.03895  -0.0399   0.0073   1.0000
  15.000   1.5592   0.04718   0.04231  -0.0396   0.0070   1.0000
  15.250   1.5520   0.05098   0.04625  -0.0399   0.0069   1.0000
  15.500   1.5419   0.05544   0.05087  -0.0408   0.0067   1.0000
  15.750   1.5329   0.06008   0.05567  -0.0422   0.0066   1.0000
  16.000   1.5220   0.06533   0.06109  -0.0442   0.0066   1.0000
  16.250   1.5087   0.07140   0.06733  -0.0469   0.0065   1.0000
  16.500   1.4930   0.07828   0.07439  -0.0504   0.0065   1.0000
  16.750   1.4744   0.08611   0.08240  -0.0546   0.0065   1.0000
  17.000   1.4538   0.09468   0.09114  -0.0594   0.0065   1.0000
  17.250   1.4301   0.10417   0.10081  -0.0648   0.0065   1.0000
  17.500   1.4050   0.11426   0.11107  -0.0707   0.0065   1.0000
  17.750   1.3792   0.12474   0.12171  -0.0769   0.0065   1.0000
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