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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 50,000
Max Cl/Cd: 32.28 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27m2-il-50000-n5.txt
Download as CSV file: xf-usa27m2-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3654   0.11352   0.10733  -0.0238   1.0000   0.1573
  -7.750  -0.3995   0.11321   0.10717  -0.0219   1.0000   0.1579
  -7.500  -0.4233   0.11183   0.10589  -0.0216   1.0000   0.1583
  -7.250  -0.4208   0.10817   0.10231  -0.0197   1.0000   0.1588
  -6.750  -0.3947   0.09031   0.08414  -0.0326   0.9878   0.0852
  -6.250  -0.3688   0.07693   0.07035  -0.0456   0.9703   0.0750
  -6.000  -0.3512   0.07282   0.06612  -0.0483   0.9624   0.0746
  -5.750  -0.3338   0.06876   0.06190  -0.0506   0.9542   0.0742
  -5.500  -0.3115   0.06461   0.05756  -0.0535   0.9470   0.0735
  -5.250  -0.2945   0.06085   0.05358  -0.0548   0.9378   0.0724
  -5.000  -0.2685   0.05643   0.04882  -0.0578   0.9313   0.0711
  -4.750  -0.2512   0.05262   0.04464  -0.0584   0.9211   0.0700
  -4.500  -0.2228   0.04863   0.04011  -0.0605   0.9144   0.0690
  -4.250  -0.1993   0.04555   0.03654  -0.0609   0.9040   0.0684
  -4.000  -0.1702   0.04294   0.03344  -0.0618   0.8943   0.0686
  -3.750  -0.1349   0.04072   0.03077  -0.0635   0.8854   0.0700
  -3.500  -0.1069   0.03896   0.02862  -0.0636   0.8736   0.0714
  -3.250  -0.0713   0.03720   0.02642  -0.0649   0.8646   0.0724
  -3.000  -0.0383   0.03574   0.02463  -0.0655   0.8543   0.0730
  -2.750  -0.0083   0.03460   0.02321  -0.0656   0.8433   0.0738
  -2.500   0.0325   0.03334   0.02165  -0.0673   0.8359   0.0749
  -2.250   0.0606   0.03248   0.02069  -0.0670   0.8237   0.0762
  -2.000   0.1008   0.03145   0.01959  -0.0688   0.8156   0.0791
  -1.750   0.1354   0.03072   0.01872  -0.0696   0.8047   0.0835
  -1.500   0.1664   0.03009   0.01798  -0.0696   0.7931   0.0881
  -1.250   0.2082   0.02913   0.01699  -0.0715   0.7854   0.0947
  -1.000   0.2343   0.02862   0.01652  -0.0707   0.7719   0.1026
  -0.750   0.2624   0.02800   0.01612  -0.0704   0.7594   0.1251
  -0.500   0.2948   0.02730   0.01586  -0.0707   0.7487   0.2386
  -0.250   0.3250   0.02689   0.01556  -0.0706   0.7366   0.3194
   0.000   0.3490   0.02642   0.01524  -0.0696   0.7225   0.3873
   0.250   0.3740   0.02572   0.01475  -0.0688   0.7092   0.4421
   0.500   0.5067   0.02423   0.01428  -0.0878   0.6967   1.0000
   0.750   0.5378   0.02409   0.01383  -0.0878   0.6824   1.0000
   1.000   0.5697   0.02397   0.01341  -0.0880   0.6683   1.0000
   1.250   0.6008   0.02392   0.01307  -0.0881   0.6539   1.0000
   1.500   0.6272   0.02403   0.01294  -0.0876   0.6387   1.0000
   1.750   0.6526   0.02422   0.01291  -0.0869   0.6239   1.0000
   2.000   0.6775   0.02446   0.01294  -0.0861   0.6099   1.0000
   2.250   0.7032   0.02471   0.01300  -0.0856   0.5968   1.0000
   2.500   0.7304   0.02496   0.01304  -0.0853   0.5846   1.0000
   2.750   0.7488   0.02540   0.01338  -0.0836   0.5715   1.0000
   3.000   0.7702   0.02580   0.01367  -0.0825   0.5601   1.0000
   3.250   0.7964   0.02611   0.01383  -0.0821   0.5503   1.0000
   3.500   0.8131   0.02664   0.01432  -0.0802   0.5395   1.0000
   3.750   0.8377   0.02699   0.01456  -0.0796   0.5308   1.0000
   4.000   0.8556   0.02751   0.01505  -0.0780   0.5213   1.0000
   4.250   0.8789   0.02793   0.01538  -0.0772   0.5134   1.0000
   4.500   0.8972   0.02848   0.01593  -0.0757   0.5052   1.0000
   4.750   0.9230   0.02887   0.01623  -0.0754   0.4987   1.0000
   5.000   0.9378   0.02955   0.01695  -0.0733   0.4907   1.0000
   5.250   0.9640   0.02992   0.01723  -0.0730   0.4842   1.0000
   5.500   0.9777   0.03065   0.01803  -0.0709   0.4765   1.0000
   5.750   1.0005   0.03108   0.01841  -0.0700   0.4694   1.0000
   6.000   1.0161   0.03173   0.01907  -0.0681   0.4615   1.0000
   6.250   1.0364   0.03215   0.01947  -0.0668   0.4532   1.0000
   6.500   1.0503   0.03278   0.02012  -0.0647   0.4446   1.0000
   6.750   1.0710   0.03318   0.02047  -0.0634   0.4362   1.0000
   7.000   1.0831   0.03391   0.02125  -0.0611   0.4279   1.0000
   7.250   1.1018   0.03446   0.02183  -0.0597   0.4205   1.0000
   7.500   1.1196   0.03515   0.02255  -0.0583   0.4141   1.0000
   7.750   1.1292   0.03608   0.02359  -0.0557   0.4069   1.0000
   8.000   1.1566   0.03645   0.02394  -0.0557   0.4008   1.0000
   8.250   1.1574   0.03771   0.02538  -0.0520   0.3938   1.0000
   8.500   1.1726   0.03850   0.02624  -0.0503   0.3873   1.0000
   8.750   1.1929   0.03917   0.02693  -0.0494   0.3813   1.0000
   9.000   1.1869   0.04064   0.02860  -0.0449   0.3744   1.0000
   9.250   1.2088   0.04117   0.02918  -0.0441   0.3680   1.0000
   9.500   1.2070   0.04262   0.03076  -0.0405   0.3614   1.0000
   9.750   1.2080   0.04399   0.03226  -0.0374   0.3543   1.0000
  10.000   1.2378   0.04416   0.03241  -0.0375   0.3482   1.0000
  10.250   1.2093   0.04709   0.03561  -0.0317   0.3409   1.0000
  10.500   1.2251   0.04790   0.03650  -0.0304   0.3345   1.0000
  10.750   1.2228   0.04986   0.03860  -0.0278   0.3284   1.0000
  11.000   1.1971   0.05353   0.04246  -0.0240   0.3213   1.0000
  11.250   1.2283   0.05336   0.04232  -0.0238   0.3162   1.0000
  11.500   1.1534   0.06183   0.05104  -0.0194   0.3073   1.0000
  11.750   1.1591   0.06372   0.05301  -0.0184   0.3016   1.0000
  12.250   1.0831   0.07834   0.06782  -0.0180   0.2845   1.0000
  12.500   1.1226   0.07607   0.06562  -0.0165   0.2825   1.0000
  12.750   1.0230   0.09404   0.08365  -0.0208   0.2680   1.0000
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