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lrn1007 (lrn1007-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: lrn1007 (lrn1007-il)
Reynolds number: 500,000
Max Cl/Cd: 125.28 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lrn1007-il-500000.txt
Download as CSV file: xf-lrn1007-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: lrn1007                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -20.000  -0.6490   0.23992   0.23756   0.0363   1.0000   0.0010
 -19.750  -0.6403   0.23694   0.23459   0.0342   1.0000   0.0010
 -19.500  -0.6315   0.23391   0.23156   0.0321   1.0000   0.0010
 -19.250  -0.6226   0.23092   0.22857   0.0300   1.0000   0.0010
 -19.000  -0.6137   0.22792   0.22558   0.0279   1.0000   0.0010
 -18.750  -0.6048   0.22490   0.22256   0.0258   1.0000   0.0010
 -18.500  -0.5960   0.22186   0.21952   0.0237   1.0000   0.0010
 -18.250  -0.5870   0.21876   0.21643   0.0216   1.0000   0.0010
 -18.000  -0.5779   0.21568   0.21336   0.0195   1.0000   0.0010
 -17.750  -0.5688   0.21257   0.21025   0.0174   1.0000   0.0010
 -17.500  -0.5597   0.20944   0.20713   0.0153   1.0000   0.0010
 -17.250  -0.5505   0.20647   0.20416   0.0132   0.9566   0.0010
 -17.000  -0.5307   0.20185   0.19947   0.0074   0.9280   0.0010
 -16.750  -0.5185   0.19832   0.19577   0.0043   0.9062   0.0009
 -16.500  -0.5101   0.19528   0.19265   0.0026   0.8950   0.0009
 -16.250  -0.5016   0.19222   0.18953   0.0009   0.8884   0.0009
 -16.000  -0.4930   0.18914   0.18641  -0.0009   0.8836   0.0009
 -15.750  -0.4845   0.18598   0.18322  -0.0027   0.8799   0.0009
 -15.500  -0.4759   0.18289   0.18009  -0.0045   0.8770   0.0009
 -15.250  -0.4671   0.17972   0.17691  -0.0063   0.8746   0.0009
 -15.000  -0.4584   0.17656   0.17373  -0.0082   0.8725   0.0009
 -14.750  -0.4498   0.17338   0.17053  -0.0100   0.8705   0.0009
 -14.500  -0.4411   0.17020   0.16733  -0.0117   0.8688   0.0009
 -14.250  -0.4326   0.16703   0.16414  -0.0135   0.8672   0.0009
 -14.000  -0.4240   0.16386   0.16095  -0.0153   0.8658   0.0009
 -13.750  -0.4154   0.16066   0.15774  -0.0170   0.8644   0.0009
 -13.500  -0.4069   0.15746   0.15454  -0.0188   0.8633   0.0009
 -13.250  -0.3982   0.15425   0.15133  -0.0206   0.8621   0.0010
 -13.000  -0.3896   0.15108   0.14815  -0.0223   0.8610   0.0010
 -12.750  -0.3811   0.14790   0.14496  -0.0241   0.8599   0.0010
 -12.500  -0.3727   0.14473   0.14179  -0.0258   0.8589   0.0010
 -12.250  -0.3642   0.14161   0.13866  -0.0275   0.8578   0.0010
 -12.000  -0.3558   0.13842   0.13547  -0.0291   0.8569   0.0010
 -11.750  -0.3474   0.13532   0.13237  -0.0308   0.8560   0.0010
 -11.500  -0.3391   0.13229   0.12933  -0.0324   0.8550   0.0010
 -11.250  -0.3308   0.12917   0.12621  -0.0340   0.8542   0.0010
 -11.000  -0.3224   0.12622   0.12320  -0.0356   0.8534   0.0010
 -10.750  -0.3143   0.12316   0.12013  -0.0372   0.8526   0.0010
 -10.500  -0.3060   0.12020   0.11716  -0.0387   0.8518   0.0010
 -10.250  -0.2976   0.11725   0.11423  -0.0403   0.8511   0.0010
 -10.000  -0.2894   0.11433   0.11131  -0.0419   0.8504   0.0010
  -9.750  -0.2811   0.11144   0.10844  -0.0434   0.8497   0.0010
  -9.500  -0.2729   0.10861   0.10562  -0.0449   0.8490   0.0010
  -9.250  -0.2648   0.10578   0.10280  -0.0464   0.8480   0.0010
  -9.000  -0.2568   0.10303   0.10007  -0.0479   0.8470   0.0010
  -8.750  -0.2489   0.10034   0.09739  -0.0493   0.8461   0.0010
  -8.500  -0.2411   0.09763   0.09469  -0.0507   0.8453   0.0010
  -8.250  -0.2335   0.09503   0.09210  -0.0521   0.8444   0.0010
  -2.500   0.1953   0.03007   0.02601  -0.1008   0.8240   0.0040
  -2.250   0.2214   0.02737   0.02318  -0.1017   0.8230   0.0045
  -2.000   0.2499   0.02536   0.02102  -0.1022   0.8220   0.0050
  -1.750   0.2790   0.02359   0.01907  -0.1023   0.8209   0.0056
  -1.500   0.3082   0.02196   0.01725  -0.1022   0.8196   0.0062
  -1.250   0.3373   0.02044   0.01554  -0.1019   0.8184   0.0066
  -1.000   0.3665   0.01908   0.01400  -0.1016   0.8174   0.0072
  -0.750   0.3957   0.01803   0.01276  -0.1010   0.8163   0.0081
  -0.500   0.4250   0.01785   0.01240  -0.1002   0.8149   0.0092
  -0.250   0.4508   0.01531   0.00964  -0.1001   0.8132   0.0150
   1.250   0.6110   0.01111   0.00500  -0.0979   0.7942   0.0263
   1.500   0.6377   0.01089   0.00472  -0.0976   0.7909   0.0206
   1.750   0.6642   0.01046   0.00420  -0.0973   0.7881   0.0180
   2.000   0.6907   0.01028   0.00400  -0.0972   0.7840   0.0160
   2.250   0.7175   0.01015   0.00379  -0.0971   0.7795   0.0154
   2.500   0.7447   0.01003   0.00361  -0.0970   0.7763   0.0178
   2.750   0.7764   0.00822   0.00371  -0.0985   0.7738   1.0000
   3.000   0.7993   0.00638   0.00158  -0.0956   0.7013   1.0000
   3.250   0.8095   0.00759   0.00160  -0.0923   0.4685   1.0000
   3.500   0.8016   0.01148   0.00312  -0.0876   0.0083   1.0000
   3.750   0.8271   0.01171   0.00343  -0.0872   0.0068   1.0000
   4.000   0.8528   0.01195   0.00389  -0.0866   0.0084   1.0000
   4.250   0.8772   0.01240   0.00458  -0.0856   0.0105   1.0000
   4.500   0.9007   0.01298   0.00534  -0.0844   0.0148   1.0000
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