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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 50,000
Max Cl/Cd: 13.23 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63145-il-50000.txt
Download as CSV file: xf-fx63145-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-145 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2642   0.12155   0.11522  -0.0294   1.0000   0.2365
  -9.500  -0.2533   0.11791   0.11163  -0.0288   1.0000   0.2449
  -9.250  -0.2770   0.11834   0.11227  -0.0298   1.0000   0.2527
  -9.000  -0.2476   0.11283   0.10675  -0.0282   1.0000   0.2627
  -8.750  -0.2440   0.11007   0.10410  -0.0276   1.0000   0.2722
  -8.500  -0.2488   0.10826   0.10243  -0.0271   1.0000   0.2835
  -8.250  -0.2599   0.10758   0.10190  -0.0261   1.0000   0.2957
  -8.000  -0.2450   0.10399   0.09840  -0.0246   1.0000   0.3094
  -7.750  -0.2348   0.10056   0.09508  -0.0235   1.0000   0.3170
  -7.500  -0.2541   0.10015   0.09491  -0.0217   1.0000   0.3274
  -7.250  -0.2405   0.09690   0.09176  -0.0198   1.0000   0.3358
  -7.000  -0.2662   0.09719   0.09232  -0.0157   1.0000   0.3437
  -6.750  -0.2854   0.09761   0.09296  -0.0101   1.0000   0.3475
  -6.500  -0.3210   0.09974   0.09528  -0.0043   1.0000   0.3532
  -5.500  -0.3625   0.06001   0.05466  -0.0708   0.9561   0.1242
  -5.250  -0.3266   0.05286   0.04655  -0.0796   0.9458   0.1050
  -5.000  -0.2783   0.04798   0.04076  -0.0866   0.9381   0.0962
  -4.750  -0.2430   0.04492   0.03726  -0.0898   0.9288   0.0936
  -4.500  -0.1934   0.04182   0.03347  -0.0946   0.9220   0.0907
  -4.250  -0.1602   0.04008   0.03117  -0.0959   0.9124   0.0889
  -4.000  -0.1113   0.03819   0.02889  -0.0989   0.9058   0.0883
  -3.750  -0.0903   0.03728   0.02795  -0.0977   0.8958   0.0892
  -3.500  -0.0489   0.03602   0.02669  -0.0988   0.8889   0.0928
  -3.250  -0.0310   0.03576   0.02631  -0.0970   0.8790   0.0965
  -3.000   0.0107   0.03464   0.02513  -0.0989   0.8722   0.1075
  -2.750   0.0349   0.03385   0.02459  -0.0999   0.8632   0.1246
  -2.500   0.0654   0.03282   0.02618  -0.0980   0.8562   0.6054
  -2.250   0.0539   0.03481   0.02826  -0.0878   0.8464   0.6692
  -2.000   0.0453   0.03621   0.02971  -0.0765   0.8386   0.7228
  -1.750   0.0317   0.03716   0.03067  -0.0675   0.8307   0.7587
  -1.500   0.0233   0.03773   0.03117  -0.0592   0.8244   0.7962
  -1.250   0.0353   0.03785   0.03110  -0.0547   0.8192   0.8286
  -1.000   0.0302   0.03829   0.03146  -0.0508   0.8122   0.8485
  -0.750   0.0430   0.03830   0.03129  -0.0481   0.8057   0.8743
  -0.500   0.0543   0.03840   0.03123  -0.0456   0.7990   0.8999
  -0.250   0.0670   0.03852   0.03123  -0.0440   0.7914   0.9268
   0.000   0.1359   0.03872   0.03107  -0.0510   0.7838   0.9617
   0.250   0.2082   0.03950   0.03157  -0.0613   0.7734   0.9854
   0.500   0.2594   0.04001   0.03184  -0.0674   0.7642   1.0000
   0.750   0.2377   0.04088   0.03269  -0.0630   0.7578   1.0000
   1.000   0.2708   0.04137   0.03299  -0.0655   0.7488   1.0000
   1.250   0.2837   0.04248   0.03399  -0.0664   0.7399   1.0000
   1.500   0.3195   0.04330   0.03466  -0.0695   0.7297   1.0000
   1.750   0.3814   0.04320   0.03432  -0.0742   0.7169   1.0000
   2.000   0.3865   0.04507   0.03616  -0.0750   0.7064   1.0000
   2.250   0.4243   0.04589   0.03684  -0.0778   0.6949   1.0000
   2.500   0.4789   0.04596   0.03678  -0.0815   0.6843   1.0000
   2.750   0.4854   0.04826   0.03905  -0.0826   0.6740   1.0000
   3.000   0.5307   0.04873   0.03942  -0.0853   0.6633   1.0000
   3.250   0.5580   0.05004   0.04068  -0.0872   0.6528   1.0000
   3.500   0.5782   0.05169   0.04229  -0.0885   0.6411   1.0000
   3.750   0.6269   0.05159   0.04212  -0.0905   0.6294   1.0000
   4.000   0.6675   0.05170   0.04221  -0.0919   0.6172   1.0000
   4.250   0.6732   0.05420   0.04469  -0.0922   0.6047   1.0000
   4.500   0.7173   0.05423   0.04469  -0.0936   0.5955   1.0000
   4.750   0.7298   0.05637   0.04683  -0.0941   0.5847   1.0000
   5.000   0.7371   0.05900   0.04946  -0.0944   0.5747   1.0000
   5.250   0.7748   0.05943   0.04993  -0.0954   0.5665   1.0000
   5.500   0.7660   0.06326   0.05377  -0.0953   0.5558   1.0000
   5.750   0.8157   0.06277   0.05331  -0.0962   0.5488   1.0000
   6.000   0.8000   0.06706   0.05762  -0.0959   0.5364   1.0000
   6.250   0.8174   0.06875   0.05933  -0.0958   0.5255   1.0000
   6.500   0.8528   0.06902   0.05969  -0.0960   0.5164   1.0000
   6.750   0.8415   0.07316   0.06387  -0.0958   0.5043   1.0000
   7.000   0.8666   0.07437   0.06513  -0.0958   0.4953   1.0000
   7.250   0.8779   0.07669   0.06752  -0.0958   0.4849   1.0000
   7.500   0.8735   0.08039   0.07125  -0.0959   0.4729   1.0000
   7.750   0.9373   0.07770   0.06872  -0.0951   0.4655   1.0000
   8.000   0.9171   0.08289   0.07394  -0.0953   0.4516   1.0000
   8.250   0.9087   0.08719   0.07829  -0.0956   0.4393   1.0000
   8.500   0.9183   0.08974   0.08091  -0.0955   0.4282   1.0000
   8.750   0.9510   0.08995   0.08126  -0.0950   0.4195   1.0000
   9.000   0.9295   0.09619   0.08754  -0.0961   0.4074   1.0000
   9.250   0.9394   0.09915   0.09057  -0.0963   0.3980   1.0000
   9.500   0.9461   0.10251   0.09401  -0.0968   0.3888   1.0000
   9.750   0.9317   0.10850   0.10005  -0.0983   0.3795   1.0000
  10.000   0.9677   0.10839   0.10006  -0.0973   0.3716   1.0000
  10.250   0.9340   0.11688   0.10857  -0.1002   0.3627   1.0000
  10.500   0.9700   0.11709   0.10893  -0.0992   0.3564   1.0000
  10.750   0.9404   0.12589   0.11771  -0.1027   0.3532   1.0000
  11.000   0.9281   0.13258   0.12445  -0.1054   0.3523   1.0000
  11.250   0.9241   0.13842   0.13035  -0.1077   0.3531   1.0000
  11.500   0.9287   0.14363   0.13565  -0.1097   0.3547   1.0000
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