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USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 50,000
Max Cl/Cd: 31.18 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40b-il-50000-n5.txt
Download as CSV file: xf-usa40b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 B 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2841   0.09951   0.09218  -0.0338   1.0000   0.0869
  -8.500  -0.2869   0.09637   0.08914  -0.0341   1.0000   0.0856
  -8.250  -0.2926   0.09321   0.08607  -0.0344   1.0000   0.0846
  -7.750  -0.3442   0.08440   0.07756  -0.0371   1.0000   0.0803
  -7.500  -0.3536   0.08135   0.07462  -0.0370   1.0000   0.0801
  -7.250  -0.3639   0.07790   0.07126  -0.0376   1.0000   0.0798
  -7.000  -0.3745   0.07417   0.06760  -0.0386   1.0000   0.0794
  -6.750  -0.3853   0.07035   0.06382  -0.0395   1.0000   0.0790
  -6.500  -0.3945   0.06649   0.05993  -0.0405   1.0000   0.0786
  -6.250  -0.4009   0.06242   0.05578  -0.0419   1.0000   0.0782
  -6.000  -0.3780   0.05578   0.04877  -0.0502   0.9911   0.0777
  -5.750  -0.3468   0.04965   0.04210  -0.0582   0.9808   0.0776
  -5.500  -0.3121   0.04473   0.03658  -0.0645   0.9706   0.0783
  -5.250  -0.2760   0.04067   0.03175  -0.0695   0.9594   0.0803
  -5.000  -0.2391   0.03867   0.02968  -0.0724   0.9473   0.0825
  -4.750  -0.1999   0.03657   0.02732  -0.0755   0.9345   0.0847
  -4.500  -0.1578   0.03433   0.02470  -0.0787   0.9223   0.0869
  -4.250  -0.1152   0.03231   0.02223  -0.0815   0.9096   0.0901
  -4.000  -0.0787   0.03093   0.02080  -0.0831   0.8952   0.0941
  -3.750  -0.0403   0.02966   0.01939  -0.0847   0.8816   0.0994
  -3.500   0.0026   0.02825   0.01784  -0.0867   0.8702   0.1048
  -3.250   0.0364   0.02729   0.01686  -0.0873   0.8547   0.1125
  -3.000   0.0690   0.02636   0.01596  -0.0876   0.8385   0.1218
  -2.750   0.1025   0.02550   0.01512  -0.0881   0.8219   0.1352
  -2.500   0.1359   0.02473   0.01437  -0.0884   0.8044   0.1548
  -2.250   0.1697   0.02395   0.01367  -0.0889   0.7862   0.1854
  -2.000   0.2030   0.02307   0.01293  -0.0893   0.7672   0.2345
  -1.750   0.2350   0.02225   0.01237  -0.0895   0.7472   0.3011
  -1.500   0.2656   0.02164   0.01198  -0.0893   0.7262   0.3804
  -1.250   0.2931   0.02119   0.01175  -0.0882   0.7041   0.4642
  -1.000   0.3133   0.02095   0.01190  -0.0854   0.6801   0.5653
  -0.750   0.3315   0.02092   0.01203  -0.0820   0.6559   0.6612
  -0.500   0.3505   0.02090   0.01195  -0.0788   0.6318   0.7305
  -0.250   0.3706   0.02082   0.01174  -0.0761   0.6075   0.7808
   0.000   0.3911   0.02069   0.01149  -0.0737   0.5822   0.8269
   0.250   0.4178   0.02051   0.01114  -0.0724   0.5578   0.8777
   0.500   0.4650   0.02043   0.01080  -0.0755   0.5305   1.0000
   0.750   0.4918   0.02074   0.01075  -0.0755   0.5095   1.0000
   1.000   0.5188   0.02110   0.01077  -0.0754   0.4907   1.0000
   1.250   0.5460   0.02150   0.01085  -0.0754   0.4741   1.0000
   1.500   0.5734   0.02193   0.01096  -0.0754   0.4595   1.0000
   1.750   0.6008   0.02238   0.01115  -0.0753   0.4458   1.0000
   2.000   0.6278   0.02287   0.01144  -0.0753   0.4330   1.0000
   2.250   0.6555   0.02336   0.01170  -0.0753   0.4223   1.0000
   2.500   0.6827   0.02389   0.01206  -0.0752   0.4118   1.0000
   2.750   0.7099   0.02443   0.01243  -0.0752   0.4026   1.0000
   3.000   0.7367   0.02499   0.01285  -0.0750   0.3935   1.0000
   3.250   0.7640   0.02557   0.01325  -0.0750   0.3859   1.0000
   3.500   0.7898   0.02619   0.01383  -0.0748   0.3778   1.0000
   3.750   0.8174   0.02680   0.01426  -0.0747   0.3715   1.0000
   4.000   0.8429   0.02749   0.01493  -0.0745   0.3649   1.0000
   4.250   0.8681   0.02818   0.01558  -0.0741   0.3584   1.0000
   4.500   0.8952   0.02882   0.01607  -0.0740   0.3530   1.0000
   4.750   0.9196   0.02961   0.01687  -0.0737   0.3474   1.0000
   5.000   0.9433   0.03043   0.01773  -0.0732   0.3419   1.0000
   5.250   0.9686   0.03121   0.01846  -0.0729   0.3374   1.0000
   5.500   0.9958   0.03194   0.01909  -0.0729   0.3336   1.0000
   5.750   1.0168   0.03297   0.02023  -0.0722   0.3290   1.0000
   6.000   1.0379   0.03399   0.02135  -0.0715   0.3243   1.0000
   6.250   1.0609   0.03490   0.02228  -0.0710   0.3201   1.0000
   6.500   1.0860   0.03573   0.02305  -0.0707   0.3167   1.0000
   6.750   1.1091   0.03677   0.02410  -0.0703   0.3136   1.0000
   7.000   1.1241   0.03825   0.02582  -0.0691   0.3099   1.0000
   7.250   1.1406   0.03968   0.02741  -0.0681   0.3065   1.0000
   7.500   1.1589   0.04096   0.02878  -0.0673   0.3032   1.0000
   7.750   1.1799   0.04207   0.02992  -0.0667   0.3003   1.0000
   8.000   1.2042   0.04304   0.03087  -0.0663   0.2977   1.0000
   8.250   1.2139   0.04489   0.03292  -0.0648   0.2947   1.0000
   8.500   1.2143   0.04729   0.03561  -0.0627   0.2914   1.0000
   8.750   1.2158   0.04970   0.03824  -0.0607   0.2886   1.0000
   9.000   1.2170   0.05212   0.04083  -0.0589   0.2860   1.0000
   9.250   1.2212   0.05434   0.04318  -0.0573   0.2836   1.0000
   9.500   1.2325   0.05609   0.04501  -0.0562   0.2814   1.0000
   9.750   1.2559   0.05718   0.04609  -0.0559   0.2794   1.0000
  10.000   0.9665   0.09158   0.08115  -0.0610   0.2674   1.0000
  10.250   0.9648   0.09609   0.08571  -0.0622   0.2650   1.0000
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