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cr001sm (cr001sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 50,000
Max Cl/Cd: 41.22 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr001sm-il-50000.txt
Download as CSV file: xf-cr001sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: cr001sm                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3519   0.10144   0.09481  -0.0237   1.0000   0.1751
  -7.250  -0.3645   0.10078   0.09430  -0.0228   1.0000   0.1805
  -7.000  -0.3861   0.10137   0.09509  -0.0242   1.0000   0.1822
  -6.750  -0.3661   0.09572   0.08943  -0.0199   1.0000   0.1933
  -6.500  -0.3817   0.09519   0.08908  -0.0219   1.0000   0.1971
  -6.250  -0.3701   0.09115   0.08506  -0.0182   1.0000   0.2078
  -6.000  -0.3708   0.08848   0.08249  -0.0171   1.0000   0.2154
  -5.750  -0.3811   0.08798   0.08209  -0.0208   1.0000   0.2253
  -5.500  -0.3756   0.08462   0.07879  -0.0172   1.0000   0.2386
  -5.250  -0.3737   0.08197   0.07622  -0.0157   1.0000   0.2527
  -5.000  -0.3723   0.07963   0.07394  -0.0153   1.0000   0.2676
  -4.750  -0.3701   0.07697   0.07136  -0.0145   1.0000   0.2839
  -4.500  -0.3660   0.07399   0.06842  -0.0110   1.0000   0.3005
  -4.250  -0.3619   0.07144   0.06593  -0.0085   1.0000   0.3198
  -4.000  -0.3586   0.06902   0.06357  -0.0078   1.0000   0.3433
  -3.750  -0.3546   0.06665   0.06125  -0.0061   1.0000   0.3710
  -3.500  -0.3512   0.06419   0.05886  -0.0027   1.0000   0.4001
  -3.250  -0.3488   0.06171   0.05647   0.0018   1.0000   0.4310
  -3.000  -0.3484   0.05953   0.05437   0.0066   1.0000   0.4725
  -2.500  -0.1129   0.03861   0.03072  -0.0633   1.0000   0.1553
  -2.250  -0.0795   0.03552   0.02720  -0.0653   1.0000   0.1455
  -2.000  -0.0438   0.03275   0.02371  -0.0671   1.0000   0.1348
  -1.750  -0.0118   0.03051   0.02086  -0.0679   1.0000   0.1289
  -1.500   0.0172   0.02891   0.01873  -0.0680   1.0000   0.1275
  -1.250   0.0418   0.02779   0.01742  -0.0677   1.0000   0.1339
  -1.000   0.0664   0.02683   0.01620  -0.0672   1.0000   0.1427
  -0.750   0.0917   0.02607   0.01520  -0.0666   1.0000   0.1517
  -0.500   0.1180   0.02542   0.01440  -0.0663   1.0000   0.1686
  -0.250   0.1464   0.02467   0.01388  -0.0666   1.0000   0.2251
   0.000   0.1703   0.02174   0.01305  -0.0648   1.0000   1.0000
   0.250   0.1905   0.02235   0.01319  -0.0644   1.0000   1.0000
   0.500   0.2100   0.02302   0.01353  -0.0641   1.0000   1.0000
   0.750   0.2290   0.02375   0.01397  -0.0638   1.0000   1.0000
   1.000   0.2473   0.02454   0.01454  -0.0636   1.0000   1.0000
   1.250   0.2652   0.02539   0.01521  -0.0634   1.0000   1.0000
   1.500   0.2827   0.02630   0.01597  -0.0632   1.0000   1.0000
   1.750   0.3277   0.02770   0.01717  -0.0682   0.9870   1.0000
   2.000   0.3766   0.02904   0.01837  -0.0737   0.9706   1.0000
   2.250   0.4202   0.03017   0.01940  -0.0780   0.9530   1.0000
   2.500   0.4646   0.03122   0.02041  -0.0822   0.9358   1.0000
   2.750   0.5115   0.03220   0.02135  -0.0865   0.9189   1.0000
   3.000   0.5497   0.03300   0.02217  -0.0892   0.9000   1.0000
   3.250   0.5902   0.03370   0.02293  -0.0920   0.8810   1.0000
   3.500   0.6390   0.03417   0.02348  -0.0957   0.8628   1.0000
   3.750   0.6731   0.03468   0.02407  -0.0969   0.8416   1.0000
   4.000   0.7211   0.03474   0.02432  -0.0997   0.8222   1.0000
   4.250   0.7605   0.03482   0.02455  -0.1009   0.8010   1.0000
   4.500   0.8113   0.03425   0.02419  -0.1031   0.7806   1.0000
   4.750   0.8588   0.03352   0.02376  -0.1044   0.7589   1.0000
   5.000   0.9137   0.03210   0.02262  -0.1058   0.7376   1.0000
   5.250   0.9554   0.03113   0.02188  -0.1054   0.7123   1.0000
   5.500   0.9998   0.02986   0.02091  -0.1049   0.6848   1.0000
   5.750   1.0434   0.02854   0.01978  -0.1040   0.6533   1.0000
   6.000   1.0760   0.02794   0.01929  -0.1021   0.6165   1.0000
   6.250   1.1066   0.02755   0.01892  -0.1000   0.5757   1.0000
   6.500   1.1317   0.02762   0.01901  -0.0974   0.5316   1.0000
   6.750   1.1538   0.02799   0.01928  -0.0947   0.4861   1.0000
   7.000   1.1741   0.02860   0.01972  -0.0920   0.4408   1.0000
   7.250   1.1925   0.02942   0.02031  -0.0893   0.3958   1.0000
   7.500   1.2068   0.03053   0.02130  -0.0863   0.3513   1.0000
   7.750   1.2197   0.03187   0.02252  -0.0833   0.3067   1.0000
   8.000   1.2314   0.03353   0.02396  -0.0802   0.2621   1.0000
   8.250   1.2428   0.03560   0.02581  -0.0774   0.2197   1.0000
   8.500   1.2555   0.03803   0.02799  -0.0748   0.1828   1.0000
   8.750   1.2684   0.04059   0.03053  -0.0724   0.1542   1.0000
   9.000   1.2865   0.04355   0.03346  -0.0708   0.1336   1.0000
   9.250   1.3034   0.04664   0.03654  -0.0693   0.1180   1.0000
   9.500   1.3143   0.05032   0.04086  -0.0667   0.1103   1.0000
   9.750   1.3270   0.05422   0.04505  -0.0649   0.1034   1.0000
  10.000   1.3272   0.05787   0.04928  -0.0618   0.0986   1.0000
  10.250   1.3453   0.06215   0.05343  -0.0612   0.0925   1.0000
  10.500   1.3384   0.06655   0.05840  -0.0579   0.0920   1.0000
  10.750   1.3280   0.07110   0.06341  -0.0548   0.0918   1.0000
  11.000   1.3148   0.07570   0.06838  -0.0520   0.0918   1.0000
  11.250   1.2988   0.08022   0.07317  -0.0493   0.0921   1.0000
  11.500   1.2815   0.08480   0.07796  -0.0470   0.0924   1.0000
  11.750   1.0465   0.09266   0.08682  -0.0426   0.1146   1.0000
  12.000   1.0151   0.10095   0.09518  -0.0459   0.1169   1.0000
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