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PT40 (pt40-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: PT40 (pt40-il)
Reynolds number: 100,000
Max Cl/Cd: 46.26 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-pt40-il-100000-n5.txt
Download as CSV file: xf-pt40-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3298   0.09578   0.09004  -0.0292   1.0000   0.0891
  -7.500  -0.3562   0.09302   0.08740  -0.0315   1.0000   0.0906
  -7.250  -0.3803   0.09001   0.08450  -0.0333   1.0000   0.0909
  -7.000  -0.3835   0.08697   0.08154  -0.0328   1.0000   0.0912
  -6.750  -0.3744   0.08501   0.07965  -0.0294   1.0000   0.0919
  -6.500  -0.3752   0.08287   0.07758  -0.0276   1.0000   0.0925
  -6.250  -0.3805   0.08065   0.07542  -0.0263   1.0000   0.0930
  -6.000  -0.3843   0.06956   0.06402  -0.0388   0.9940   0.0751
  -5.750  -0.3591   0.06633   0.06078  -0.0416   0.9878   0.0743
  -5.500  -0.3328   0.06155   0.05586  -0.0473   0.9806   0.0738
  -5.250  -0.3066   0.05689   0.05104  -0.0523   0.9725   0.0729
  -5.000  -0.2812   0.05177   0.04566  -0.0569   0.9637   0.0712
  -4.750  -0.2511   0.04579   0.03920  -0.0624   0.9570   0.0698
  -4.500  -0.2247   0.04325   0.03650  -0.0640   0.9477   0.0706
  -4.250  -0.1907   0.04039   0.03341  -0.0671   0.9426   0.0717
  -4.000  -0.1639   0.03767   0.03039  -0.0684   0.9329   0.0721
  -3.750  -0.1294   0.03486   0.02723  -0.0708   0.9276   0.0722
  -3.500  -0.1018   0.03270   0.02479  -0.0715   0.9181   0.0726
  -3.250  -0.0678   0.03063   0.02235  -0.0731   0.9118   0.0738
  -3.000  -0.0381   0.02877   0.01999  -0.0736   0.9029   0.0753
  -2.750  -0.0054   0.02753   0.01872  -0.0746   0.8955   0.0761
  -2.500   0.0267   0.02638   0.01744  -0.0754   0.8878   0.0768
  -2.250   0.0575   0.02534   0.01628  -0.0758   0.8787   0.0777
  -2.000   0.0924   0.02432   0.01512  -0.0768   0.8720   0.0792
  -1.750   0.1207   0.02353   0.01415  -0.0766   0.8610   0.0811
  -1.500   0.1557   0.02262   0.01300  -0.0774   0.8539   0.0828
  -1.250   0.1831   0.02192   0.01232  -0.0770   0.8423   0.0838
  -1.000   0.2163   0.02120   0.01160  -0.0776   0.8343   0.0851
  -0.750   0.2439   0.02072   0.01111  -0.0771   0.8223   0.0871
  -0.500   0.2763   0.02017   0.01047  -0.0774   0.8135   0.0898
  -0.250   0.3033   0.01971   0.01000  -0.0767   0.7998   0.0916
   0.000   0.3319   0.01917   0.00950  -0.0762   0.7839   0.0934
   0.250   0.3594   0.01869   0.00901  -0.0752   0.7636   0.0957
   0.500   0.3862   0.01832   0.00858  -0.0742   0.7423   0.0989
   0.750   0.4130   0.01795   0.00823  -0.0734   0.7244   0.1019
   1.000   0.4399   0.01763   0.00794  -0.0726   0.7086   0.1048
   1.250   0.4656   0.01743   0.00773  -0.0716   0.6910   0.1085
   1.500   0.4914   0.01722   0.00754  -0.0707   0.6733   0.1130
   1.750   0.5174   0.01707   0.00739  -0.0698   0.6550   0.1185
   2.000   0.5434   0.01694   0.00723  -0.0689   0.6356   0.1245
   2.250   0.5694   0.01684   0.00711  -0.0680   0.6148   0.1345
   2.750   0.6108   0.01493   0.00718  -0.0645   0.5715   0.7358
   3.250   0.6781   0.01502   0.00712  -0.0652   0.5112   1.0000
   3.500   0.7012   0.01532   0.00720  -0.0639   0.4793   1.0000
   3.750   0.7235   0.01569   0.00732  -0.0625   0.4441   1.0000
   4.000   0.7452   0.01611   0.00750  -0.0610   0.4058   1.0000
   4.250   0.7663   0.01661   0.00773  -0.0596   0.3676   1.0000
   4.500   0.7872   0.01716   0.00802  -0.0581   0.3347   1.0000
   4.750   0.8084   0.01773   0.00837  -0.0568   0.3094   1.0000
   5.000   0.8300   0.01829   0.00876  -0.0555   0.2894   1.0000
   5.250   0.8517   0.01886   0.00918  -0.0543   0.2739   1.0000
   5.500   0.8738   0.01942   0.00962  -0.0532   0.2607   1.0000
   5.750   0.8963   0.01996   0.01010  -0.0521   0.2495   1.0000
   6.000   0.9177   0.02058   0.01057  -0.0509   0.2394   1.0000
   6.250   0.9403   0.02109   0.01107  -0.0499   0.2282   1.0000
   6.500   0.9618   0.02166   0.01156  -0.0488   0.2172   1.0000
   6.750   0.9822   0.02226   0.01204  -0.0476   0.2056   1.0000
   7.000   1.0037   0.02274   0.01252  -0.0465   0.1936   1.0000
   7.250   1.0246   0.02329   0.01304  -0.0453   0.1837   1.0000
   7.500   1.0448   0.02387   0.01357  -0.0441   0.1754   1.0000
   7.750   1.0660   0.02441   0.01415  -0.0430   0.1670   1.0000
   8.000   1.0850   0.02503   0.01472  -0.0416   0.1594   1.0000
   8.250   1.1054   0.02558   0.01534  -0.0404   0.1507   1.0000
   8.500   1.1242   0.02621   0.01597  -0.0391   0.1424   1.0000
   8.750   1.1414   0.02689   0.01662  -0.0376   0.1342   1.0000
   9.000   1.1593   0.02755   0.01735  -0.0361   0.1248   1.0000
   9.250   1.1756   0.02830   0.01811  -0.0345   0.1154   1.0000
   9.500   1.1897   0.02911   0.01892  -0.0326   0.1063   1.0000
   9.750   1.2023   0.03001   0.01983  -0.0306   0.0981   1.0000
  10.000   1.2138   0.03103   0.02083  -0.0285   0.0912   1.0000
  10.250   1.2240   0.03216   0.02192  -0.0265   0.0859   1.0000
  10.500   1.2345   0.03334   0.02315  -0.0245   0.0812   1.0000
  10.750   1.2429   0.03466   0.02447  -0.0226   0.0780   1.0000
  11.000   1.2518   0.03602   0.02590  -0.0208   0.0748   1.0000
  11.250   1.2587   0.03751   0.02740  -0.0190   0.0725   1.0000
  11.500   1.2658   0.03908   0.02904  -0.0174   0.0703   1.0000
  11.750   1.2724   0.04074   0.03079  -0.0160   0.0683   1.0000
  12.000   1.2776   0.04254   0.03263  -0.0146   0.0667   1.0000
  12.250   1.2815   0.04450   0.03460  -0.0134   0.0654   1.0000
  12.500   1.2868   0.04648   0.03672  -0.0124   0.0640   1.0000
  12.750   1.2911   0.04860   0.03894  -0.0114   0.0628   1.0000
  13.000   1.2945   0.05084   0.04128  -0.0107   0.0618   1.0000
  13.250   1.2973   0.05318   0.04369  -0.0100   0.0609   1.0000
  13.500   1.2997   0.05562   0.04617  -0.0095   0.0602   1.0000
  13.750   1.3023   0.05808   0.04867  -0.0091   0.0596   1.0000
  14.000   1.3034   0.06088   0.05164  -0.0088   0.0589   1.0000
  14.250   1.3032   0.06387   0.05479  -0.0087   0.0582   1.0000
  14.500   1.3018   0.06707   0.05814  -0.0089   0.0575   1.0000
  14.750   1.2993   0.07047   0.06169  -0.0093   0.0569   1.0000
  15.000   1.2958   0.07405   0.06541  -0.0099   0.0563   1.0000
  15.250   1.2918   0.07780   0.06927  -0.0107   0.0557   1.0000
  15.500   1.2879   0.08163   0.07321  -0.0116   0.0552   1.0000
  15.750   1.2851   0.08534   0.07700  -0.0126   0.0547   1.0000
  16.000   1.2846   0.08872   0.08042  -0.0134   0.0542   1.0000
  16.250   1.2726   0.09421   0.08611  -0.0157   0.0539   1.0000
  16.500   1.2537   0.10121   0.09338  -0.0192   0.0536   1.0000
  16.750   1.2292   0.10962   0.10207  -0.0239   0.0534   1.0000
  17.000   1.1916   0.12138   0.11416  -0.0312   0.0534   1.0000
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