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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 500,000
Max Cl/Cd: 86.84 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27m2-il-500000.txt
Download as CSV file: xf-usa27m2-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 mod. AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2048   0.08947   0.08714  -0.0698   0.9838   0.0306
  -9.000  -0.1944   0.08564   0.08332  -0.0733   0.9797   0.0313
  -8.750  -0.1835   0.08093   0.07861  -0.0785   0.9758   0.0324
  -8.500  -0.2078   0.06610   0.06374  -0.0981   0.9642   0.0342
  -8.250  -0.1863   0.06354   0.06116  -0.1006   0.9617   0.0346
  -8.000  -0.1611   0.06047   0.05805  -0.1049   0.9598   0.0350
  -7.750  -0.1442   0.05734   0.05489  -0.1077   0.9551   0.0355
  -7.500  -0.1312   0.05385   0.05134  -0.1101   0.9485   0.0362
  -7.250  -0.1134   0.04876   0.04613  -0.1145   0.9446   0.0375
  -7.000  -0.1369   0.03593   0.03253  -0.1161   0.9321   0.0409
  -6.750  -0.1108   0.03414   0.03073  -0.1171   0.9290   0.0415
  -6.500  -0.0975   0.03279   0.02932  -0.1153   0.9206   0.0422
  -6.250  -0.0762   0.03072   0.02707  -0.1153   0.9153   0.0438
  -6.000  -0.0716   0.02775   0.02351  -0.1121   0.9058   0.0480
  -5.750  -0.0458   0.02634   0.02213  -0.1124   0.9002   0.0491
  -5.500  -0.0245   0.02528   0.02101  -0.1116   0.8930   0.0509
  -5.250  -0.0086   0.02376   0.01901  -0.1096   0.8852   0.0564
  -5.000   0.0157   0.02247   0.01778  -0.1093   0.8780   0.0578
  -4.750   0.0389   0.02168   0.01689  -0.1086   0.8697   0.0608
  -4.500   0.0588   0.02048   0.01544  -0.1072   0.8613   0.0670
  -4.250   0.0836   0.01960   0.01455  -0.1068   0.8527   0.0698
  -4.000   0.1036   0.01880   0.01350  -0.1053   0.8430   0.0782
  -3.750   0.1337   0.01514   0.00901  -0.1030   0.8345   0.0444
  -3.500   0.1586   0.01428   0.00783  -0.1016   0.8230   0.0405
  -3.250   0.1847   0.01420   0.00765  -0.1009   0.8107   0.0400
  -3.000   0.2107   0.01306   0.00646  -0.1003   0.7978   0.0392
  -2.750   0.2356   0.01249   0.00582  -0.0995   0.7830   0.0390
  -2.500   0.2594   0.01206   0.00531  -0.0984   0.7657   0.0390
  -2.250   0.2825   0.01171   0.00488  -0.0972   0.7450   0.0391
  -2.000   0.3046   0.01145   0.00451  -0.0958   0.7210   0.0392
  -1.750   0.3260   0.01127   0.00420  -0.0942   0.6958   0.0394
  -1.500   0.3468   0.01115   0.00395  -0.0926   0.6729   0.0396
  -1.250   0.3681   0.01110   0.00377  -0.0911   0.6538   0.0400
  -0.750   0.4111   0.01079   0.00329  -0.0882   0.6229   0.0417
  -0.500   0.4339   0.01071   0.00316  -0.0871   0.6094   0.0424
  -0.250   0.4567   0.01068   0.00306  -0.0859   0.5960   0.0435
   0.000   0.4793   0.01067   0.00298  -0.0847   0.5816   0.0448
   0.250   0.5016   0.01069   0.00292  -0.0835   0.5651   0.0463
   0.500   0.5233   0.01071   0.00286  -0.0821   0.5461   0.0494
   0.750   0.5440   0.01070   0.00284  -0.0805   0.5245   0.0633
   1.000   0.5601   0.01040   0.00290  -0.0783   0.5029   0.2159
   1.250   0.5797   0.01045   0.00301  -0.0767   0.4808   0.2721
   1.500   0.5999   0.01058   0.00311  -0.0751   0.4609   0.3076
   1.750   0.6207   0.01070   0.00322  -0.0738   0.4447   0.3420
   2.000   0.6419   0.01079   0.00332  -0.0725   0.4320   0.3754
   2.250   0.6601   0.01054   0.00337  -0.0708   0.4223   0.4958
   2.500   0.7335   0.01022   0.00419  -0.0803   0.4104   0.9743
   2.750   0.8098   0.01074   0.00456  -0.0910   0.4000   0.9896
   3.000   0.8822   0.01102   0.00473  -0.1009   0.3910   0.9980
   3.250   0.9169   0.01123   0.00485  -0.1027   0.3847   1.0000
   3.500   0.9370   0.01134   0.00495  -0.1011   0.3795   1.0000
   3.750   0.9558   0.01149   0.00507  -0.0994   0.3745   1.0000
   4.000   0.9734   0.01171   0.00522  -0.0974   0.3698   1.0000
   4.250   0.9930   0.01181   0.00533  -0.0958   0.3660   1.0000
   4.500   1.0119   0.01194   0.00546  -0.0941   0.3618   1.0000
   4.750   1.0295   0.01211   0.00559  -0.0921   0.3575   1.0000
   5.000   1.0457   0.01234   0.00577  -0.0898   0.3529   1.0000
   5.250   1.0642   0.01243   0.00590  -0.0880   0.3494   1.0000
   5.500   1.0818   0.01256   0.00604  -0.0860   0.3457   1.0000
   5.750   1.0980   0.01272   0.00619  -0.0837   0.3421   1.0000
   6.000   1.1116   0.01291   0.00636  -0.0809   0.3386   1.0000
   6.250   1.1256   0.01309   0.00653  -0.0782   0.3353   1.0000
   6.500   1.1407   0.01319   0.00667  -0.0757   0.3321   1.0000
   6.750   1.1553   0.01331   0.00682  -0.0732   0.3276   1.0000
   7.000   1.1686   0.01352   0.00699  -0.0704   0.3226   1.0000
   7.250   1.1841   0.01370   0.00718  -0.0681   0.3178   1.0000
   7.500   1.2010   0.01383   0.00735  -0.0661   0.3126   1.0000
   7.750   1.2157   0.01406   0.00756  -0.0637   0.3068   1.0000
   8.000   1.2323   0.01427   0.00779  -0.0617   0.3014   1.0000
   8.250   1.2499   0.01446   0.00800  -0.0600   0.2952   1.0000
   8.500   1.2649   0.01477   0.00828  -0.0578   0.2891   1.0000
   8.750   1.2838   0.01497   0.00854  -0.0564   0.2824   1.0000
   9.000   1.2990   0.01532   0.00885  -0.0544   0.2733   1.0000
   9.250   1.3164   0.01561   0.00915  -0.0528   0.2614   1.0000
   9.500   1.3317   0.01603   0.00953  -0.0510   0.2469   1.0000
   9.750   1.3448   0.01659   0.01001  -0.0489   0.2293   1.0000
  10.000   1.3563   0.01727   0.01059  -0.0467   0.2094   1.0000
  10.250   1.3662   0.01808   0.01129  -0.0443   0.1926   1.0000
  10.500   1.3758   0.01894   0.01208  -0.0419   0.1792   1.0000
  10.750   1.3852   0.01983   0.01292  -0.0397   0.1680   1.0000
  11.250   1.4048   0.02168   0.01470  -0.0355   0.1464   1.0000
  11.500   1.4128   0.02275   0.01570  -0.0334   0.1312   1.0000
  11.750   1.4135   0.02434   0.01710  -0.0306   0.1010   1.0000
  12.000   1.3941   0.02737   0.01985  -0.0261   0.0607   1.0000
  12.250   1.3743   0.03069   0.02302  -0.0221   0.0278   1.0000
  12.500   1.3751   0.03264   0.02503  -0.0203   0.0237   1.0000
  12.750   1.3778   0.03453   0.02700  -0.0187   0.0221   1.0000
  13.000   1.3793   0.03662   0.02918  -0.0174   0.0209   1.0000
  13.250   1.3827   0.03864   0.03130  -0.0163   0.0202   1.0000
  13.500   1.3847   0.04089   0.03366  -0.0154   0.0195   1.0000
  13.750   1.3851   0.04341   0.03629  -0.0146   0.0190   1.0000
  14.000   1.3834   0.04628   0.03927  -0.0141   0.0186   1.0000
  14.250   1.3794   0.04950   0.04260  -0.0137   0.0182   1.0000
  14.500   1.3726   0.05318   0.04639  -0.0135   0.0179   1.0000
  14.750   1.3631   0.05729   0.05063  -0.0135   0.0176   1.0000
  15.000   1.3513   0.06180   0.05527  -0.0137   0.0173   1.0000
  15.250   1.3390   0.06652   0.06013  -0.0142   0.0172   1.0000
  15.500   1.3309   0.07079   0.06451  -0.0147   0.0170   1.0000
  15.750   1.3215   0.07535   0.06919  -0.0154   0.0169   1.0000
  16.000   1.3110   0.08011   0.07407  -0.0163   0.0168   1.0000
  16.250   1.3002   0.08503   0.07910  -0.0173   0.0166   1.0000
  16.500   1.2889   0.09006   0.08424  -0.0185   0.0165   1.0000
  16.750   1.2778   0.09509   0.08938  -0.0196   0.0164   1.0000
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