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PT40 (pt40-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: PT40 (pt40-il)
Reynolds number: 500,000
Max Cl/Cd: 78.83 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-pt40-il-500000.txt
Download as CSV file: xf-pt40-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PT40                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3397   0.09183   0.08918  -0.0297   1.0000   0.0501
  -8.000  -0.4119   0.08258   0.08000  -0.0372   1.0000   0.0522
  -7.750  -0.4168   0.08077   0.07825  -0.0343   1.0000   0.0523
  -7.500  -0.4230   0.07900   0.07652  -0.0320   1.0000   0.0524
  -7.250  -0.4090   0.07657   0.07411  -0.0331   0.9986   0.0526
  -7.000  -0.3843   0.07355   0.07108  -0.0368   0.9959   0.0529
  -6.750  -0.3656   0.05609   0.05312  -0.0643   0.9857   0.0572
  -6.500  -0.3384   0.05360   0.05068  -0.0663   0.9836   0.0574
  -6.250  -0.3114   0.05152   0.04862  -0.0683   0.9803   0.0577
  -6.000  -0.2845   0.04945   0.04655  -0.0704   0.9756   0.0580
  -5.750  -0.2542   0.04714   0.04420  -0.0734   0.9727   0.0585
  -5.500  -0.2312   0.03834   0.03473  -0.0804   0.9646   0.0630
  -5.250  -0.2015   0.03665   0.03308  -0.0819   0.9599   0.0633
  -5.000  -0.1729   0.03510   0.03154  -0.0832   0.9541   0.0637
  -4.750  -0.1461   0.03354   0.02993  -0.0839   0.9455   0.0643
  -4.500  -0.1234   0.02942   0.02509  -0.0847   0.9337   0.0690
  -4.250  -0.0957   0.02762   0.02332  -0.0854   0.9252   0.0694
  -4.000  -0.0758   0.02204   0.01705  -0.0847   0.9122   0.0633
  -3.750  -0.0496   0.02066   0.01562  -0.0844   0.8997   0.0612
  -3.500  -0.0242   0.01854   0.01319  -0.0839   0.8877   0.0603
  -3.250   0.0017   0.01699   0.01135  -0.0833   0.8751   0.0603
  -3.000   0.0282   0.01600   0.01015  -0.0828   0.8623   0.0611
  -2.750   0.0552   0.01514   0.00906  -0.0822   0.8505   0.0618
  -2.500   0.0823   0.01446   0.00819  -0.0816   0.8382   0.0623
  -2.250   0.1093   0.01377   0.00734  -0.0811   0.8260   0.0629
  -2.000   0.1360   0.01319   0.00670  -0.0806   0.8114   0.0636
  -1.750   0.1627   0.01287   0.00634  -0.0799   0.7945   0.0644
  -1.500   0.1896   0.01259   0.00602  -0.0793   0.7780   0.0653
  -1.250   0.2166   0.01233   0.00569  -0.0787   0.7621   0.0665
  -1.000   0.2437   0.01208   0.00533  -0.0781   0.7469   0.0677
  -0.750   0.2712   0.01188   0.00503  -0.0776   0.7330   0.0685
  -0.500   0.2981   0.01139   0.00454  -0.0771   0.7197   0.0696
  -0.250   0.3251   0.01118   0.00431  -0.0766   0.7063   0.0707
   0.000   0.3524   0.01101   0.00413  -0.0761   0.6918   0.0720
   0.250   0.3798   0.01087   0.00397  -0.0756   0.6774   0.0736
   0.500   0.4071   0.01081   0.00384  -0.0751   0.6622   0.0751
   0.750   0.4335   0.01055   0.00356  -0.0745   0.6464   0.0767
   1.000   0.4605   0.01043   0.00344  -0.0740   0.6291   0.0783
   1.250   0.4874   0.01036   0.00335  -0.0734   0.6105   0.0802
   1.500   0.5143   0.01036   0.00328  -0.0729   0.5915   0.0823
   1.750   0.5407   0.01025   0.00315  -0.0723   0.5712   0.0848
   2.000   0.5670   0.01027   0.00312  -0.0717   0.5489   0.0875
   2.250   0.5932   0.01035   0.00310  -0.0710   0.5255   0.0902
   2.500   0.6194   0.01035   0.00307  -0.0704   0.5008   0.0939
   2.750   0.6452   0.01047   0.00310  -0.0697   0.4715   0.0986
   3.000   0.6704   0.01061   0.00313  -0.0690   0.4353   0.1047
   3.250   0.6941   0.01091   0.00323  -0.0680   0.3838   0.1143
   3.500   0.7141   0.01031   0.00348  -0.0671   0.3272   0.5322
   3.750   0.7427   0.00977   0.00381  -0.0669   0.2803   1.0000
   4.000   0.7664   0.01016   0.00402  -0.0659   0.2547   1.0000
   4.250   0.7909   0.01049   0.00421  -0.0651   0.2366   1.0000
   4.500   0.8155   0.01083   0.00442  -0.0643   0.2220   1.0000
   4.750   0.8409   0.01109   0.00461  -0.0636   0.2105   1.0000
   5.000   0.8661   0.01136   0.00481  -0.0629   0.2005   1.0000
   5.250   0.8909   0.01167   0.00503  -0.0621   0.1910   1.0000
   5.500   0.9165   0.01191   0.00523  -0.0615   0.1833   1.0000
   5.750   0.9412   0.01222   0.00547  -0.0607   0.1752   1.0000
   6.000   0.9669   0.01245   0.00568  -0.0601   0.1690   1.0000
   6.250   0.9917   0.01274   0.00591  -0.0594   0.1621   1.0000
   6.500   1.0169   0.01300   0.00615  -0.0587   0.1559   1.0000
   6.750   1.0417   0.01329   0.00639  -0.0580   0.1490   1.0000
   7.000   1.0666   0.01355   0.00664  -0.0573   0.1425   1.0000
   7.250   1.0908   0.01388   0.00690  -0.0565   0.1351   1.0000
   7.500   1.1155   0.01415   0.00716  -0.0558   0.1270   1.0000
   7.750   1.1394   0.01450   0.00744  -0.0550   0.1165   1.0000
   8.000   1.1619   0.01495   0.00779  -0.0540   0.1007   1.0000
   8.250   1.1814   0.01564   0.00829  -0.0526   0.0766   1.0000
   8.500   1.2002   0.01638   0.00890  -0.0511   0.0634   1.0000
   8.750   1.2199   0.01702   0.00948  -0.0497   0.0581   1.0000
   9.000   1.2393   0.01765   0.01008  -0.0483   0.0548   1.0000
   9.250   1.2590   0.01822   0.01066  -0.0469   0.0526   1.0000
   9.500   1.2780   0.01880   0.01125  -0.0454   0.0508   1.0000
   9.750   1.2945   0.01953   0.01196  -0.0436   0.0494   1.0000
  10.000   1.3106   0.02016   0.01263  -0.0416   0.0484   1.0000
  10.250   1.3264   0.02077   0.01327  -0.0397   0.0475   1.0000
  10.500   1.3412   0.02144   0.01397  -0.0376   0.0466   1.0000
  10.750   1.3551   0.02217   0.01473  -0.0356   0.0459   1.0000
  11.000   1.3670   0.02305   0.01562  -0.0334   0.0452   1.0000
  11.250   1.3759   0.02413   0.01672  -0.0309   0.0445   1.0000
  11.500   1.3860   0.02518   0.01781  -0.0288   0.0440   1.0000
  11.750   1.3988   0.02608   0.01878  -0.0271   0.0436   1.0000
  12.000   1.4103   0.02709   0.01985  -0.0253   0.0432   1.0000
  12.250   1.4210   0.02820   0.02102  -0.0236   0.0427   1.0000
  12.500   1.4310   0.02940   0.02228  -0.0220   0.0422   1.0000
  12.750   1.4404   0.03069   0.02362  -0.0205   0.0418   1.0000
  13.000   1.4489   0.03210   0.02507  -0.0191   0.0414   1.0000
  13.250   1.4565   0.03363   0.02665  -0.0178   0.0409   1.0000
  13.500   1.4629   0.03533   0.02838  -0.0166   0.0406   1.0000
  13.750   1.4678   0.03720   0.03029  -0.0154   0.0403   1.0000
  14.000   1.4713   0.03927   0.03239  -0.0141   0.0399   1.0000
  14.250   1.4769   0.04118   0.03436  -0.0131   0.0397   1.0000
  14.500   1.4835   0.04303   0.03630  -0.0124   0.0395   1.0000
  14.750   1.4894   0.04500   0.03836  -0.0117   0.0393   1.0000
  15.000   1.4944   0.04709   0.04053  -0.0111   0.0390   1.0000
  15.250   1.4987   0.04928   0.04281  -0.0106   0.0388   1.0000
  15.500   1.5025   0.05157   0.04518  -0.0102   0.0386   1.0000
  15.750   1.5058   0.05394   0.04764  -0.0099   0.0384   1.0000
  16.000   1.5085   0.05644   0.05022  -0.0097   0.0382   1.0000
  16.250   1.5105   0.05906   0.05292  -0.0096   0.0380   1.0000
  16.500   1.5121   0.06177   0.05572  -0.0097   0.0377   1.0000
  16.750   1.5135   0.06457   0.05860  -0.0098   0.0376   1.0000
  17.000   1.5144   0.06747   0.06158  -0.0100   0.0374   1.0000
  17.250   1.5147   0.07050   0.06469  -0.0104   0.0372   1.0000
  17.500   1.5147   0.07360   0.06787  -0.0109   0.0370   1.0000
  17.750   1.5148   0.07675   0.07109  -0.0115   0.0367   1.0000
  18.000   1.5147   0.07993   0.07433  -0.0122   0.0365   1.0000
  18.250   1.5153   0.08301   0.07747  -0.0128   0.0363   1.0000
  18.500   1.5162   0.08599   0.08050  -0.0132   0.0361   1.0000
  18.750   1.5180   0.08881   0.08337  -0.0135   0.0360   1.0000
  19.000   1.5199   0.09155   0.08616  -0.0136   0.0358   1.0000
  19.250   1.5185   0.09487   0.08956  -0.0141   0.0356   1.0000
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