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USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 41 AIRFOIL (usa41-il)
Reynolds number: 500,000
Max Cl/Cd: 104.58 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa41-il-500000-n5.txt
Download as CSV file: xf-usa41-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 41 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3448   0.08997   0.08777  -0.0261   1.0000   0.0074
  -8.000  -0.3504   0.08629   0.08414  -0.0262   1.0000   0.0072
  -7.750  -0.3507   0.08461   0.08250  -0.0253   1.0000   0.0075
  -7.250  -0.3261   0.07608   0.07400  -0.0347   0.9895   0.0077
  -7.000  -0.3047   0.07119   0.06910  -0.0418   0.9803   0.0081
  -6.750  -0.2807   0.06512   0.06300  -0.0510   0.9702   0.0090
  -6.500  -0.2472   0.05447   0.05227  -0.0672   0.9601   0.0097
  -6.250  -0.2081   0.04712   0.04480  -0.0798   0.9529   0.0103
  -6.000  -0.1663   0.01687   0.01269  -0.1050   0.9376   0.0138
  -5.750  -0.1356   0.01667   0.01241  -0.1058   0.9300   0.0146
  -5.500  -0.1036   0.01697   0.01272  -0.1067   0.9232   0.0154
  -5.250  -0.0751   0.01622   0.01175  -0.1071   0.9145   0.0167
  -5.000  -0.0471   0.01497   0.01012  -0.1072   0.9062   0.0189
  -4.750  -0.0187   0.01484   0.00978  -0.1072   0.8973   0.0200
  -4.500   0.0066   0.01357   0.00832  -0.1071   0.8881   0.0213
  -4.250   0.0334   0.01319   0.00783  -0.1069   0.8790   0.0223
  -4.000   0.0599   0.01284   0.00737  -0.1066   0.8690   0.0236
  -3.750   0.0862   0.01233   0.00672  -0.1062   0.8584   0.0248
  -3.500   0.1126   0.01183   0.00605  -0.1058   0.8470   0.0259
  -3.250   0.1391   0.01151   0.00559  -0.1054   0.8345   0.0271
  -3.000   0.1654   0.01116   0.00510  -0.1049   0.8203   0.0277
  -2.750   0.1915   0.01081   0.00462  -0.1044   0.8041   0.0280
  -2.500   0.2176   0.01052   0.00420  -0.1038   0.7861   0.0283
  -2.250   0.2434   0.01026   0.00379  -0.1032   0.7671   0.0285
  -2.000   0.2693   0.01005   0.00346  -0.1027   0.7473   0.0287
  -1.750   0.2944   0.00957   0.00284  -0.1020   0.7269   0.0294
  -1.500   0.3199   0.00937   0.00251  -0.1014   0.7068   0.0295
  -1.250   0.3455   0.00920   0.00224  -0.1008   0.6854   0.0296
  -1.000   0.3710   0.00907   0.00199  -0.1002   0.6641   0.0298
  -0.750   0.3967   0.00897   0.00177  -0.0996   0.6425   0.0302
  -0.500   0.4223   0.00892   0.00160  -0.0990   0.6206   0.0310
  -0.250   0.4481   0.00889   0.00146  -0.0985   0.6000   0.0322
   0.000   0.4740   0.00889   0.00137  -0.0980   0.5809   0.0337
   0.250   0.5000   0.00893   0.00131  -0.0975   0.5631   0.0352
   0.500   0.5261   0.00898   0.00128  -0.0971   0.5475   0.0367
   0.750   0.5523   0.00904   0.00126  -0.0967   0.5336   0.0381
   1.250   0.6049   0.00910   0.00131  -0.0959   0.5082   0.0596
   1.500   0.6307   0.00898   0.00145  -0.0956   0.4973   0.1682
   1.750   0.6569   0.00907   0.00154  -0.0952   0.4860   0.1883
   2.000   0.6833   0.00915   0.00161  -0.0949   0.4747   0.1962
   2.250   0.7097   0.00923   0.00169  -0.0945   0.4640   0.2055
   2.500   0.7359   0.00931   0.00178  -0.0942   0.4528   0.2140
   2.750   0.7619   0.00940   0.00187  -0.0938   0.4411   0.2243
   3.000   0.7877   0.00948   0.00198  -0.0934   0.4280   0.2464
   3.500   0.8522   0.00841   0.00240  -0.0959   0.3983   1.0000
   4.000   0.9037   0.00876   0.00270  -0.0950   0.3746   1.0000
   4.250   0.9294   0.00894   0.00287  -0.0946   0.3652   1.0000
   4.500   0.9548   0.00914   0.00305  -0.0941   0.3544   1.0000
   4.750   0.9799   0.00937   0.00324  -0.0936   0.3393   1.0000
   5.000   1.0036   0.00973   0.00348  -0.0929   0.3092   1.0000
   5.250   1.0269   0.01013   0.00375  -0.0921   0.2762   1.0000
   5.500   1.0495   0.01061   0.00406  -0.0913   0.2393   1.0000
   5.750   1.0708   0.01126   0.00446  -0.0903   0.1903   1.0000
   6.000   1.0872   0.01246   0.00520  -0.0886   0.1045   1.0000
   6.500   1.1246   0.01434   0.00662  -0.0859   0.0210   1.0000
   6.750   1.1471   0.01483   0.00712  -0.0850   0.0163   1.0000
   7.000   1.1687   0.01541   0.00775  -0.0839   0.0125   1.0000
   7.250   1.1909   0.01588   0.00832  -0.0830   0.0113   1.0000
   7.500   1.2124   0.01642   0.00893  -0.0819   0.0103   1.0000
   7.750   1.2326   0.01707   0.00963  -0.0807   0.0092   1.0000
   8.000   1.2506   0.01792   0.01056  -0.0792   0.0082   1.0000
   8.250   1.2707   0.01849   0.01121  -0.0780   0.0076   1.0000
   8.500   1.2890   0.01922   0.01203  -0.0766   0.0071   1.0000
   8.750   1.3063   0.02000   0.01291  -0.0750   0.0067   1.0000
   9.000   1.3229   0.02078   0.01376  -0.0733   0.0062   1.0000
   9.250   1.3375   0.02168   0.01473  -0.0714   0.0059   1.0000
   9.500   1.3474   0.02290   0.01605  -0.0689   0.0057   1.0000
   9.750   1.3541   0.02417   0.01743  -0.0658   0.0054   1.0000
  10.000   1.3625   0.02516   0.01853  -0.0629   0.0053   1.0000
  10.250   1.3705   0.02619   0.01967  -0.0602   0.0050   1.0000
  10.500   1.3779   0.02730   0.02089  -0.0575   0.0048   1.0000
  10.750   1.3846   0.02850   0.02220  -0.0550   0.0045   1.0000
  11.000   1.3895   0.02990   0.02371  -0.0526   0.0044   1.0000
  11.250   1.3953   0.03128   0.02522  -0.0505   0.0042   1.0000
  11.500   1.3993   0.03290   0.02695  -0.0485   0.0041   1.0000
  11.750   1.4009   0.03486   0.02903  -0.0465   0.0040   1.0000
  12.000   1.4045   0.03667   0.03094  -0.0450   0.0039   1.0000
  12.250   1.4046   0.03897   0.03336  -0.0436   0.0038   1.0000
  12.500   1.4040   0.04147   0.03598  -0.0425   0.0037   1.0000
  12.750   1.4008   0.04445   0.03910  -0.0415   0.0037   1.0000
  13.000   1.3947   0.04794   0.04276  -0.0408   0.0036   1.0000
  13.250   1.3902   0.05142   0.04640  -0.0406   0.0035   1.0000
  13.500   1.3858   0.05505   0.05022  -0.0406   0.0035   1.0000
  13.750   1.3803   0.05898   0.05433  -0.0411   0.0035   1.0000
  14.000   1.3729   0.06336   0.05891  -0.0419   0.0034   1.0000
  14.250   1.3641   0.06812   0.06385  -0.0431   0.0034   1.0000
  14.500   1.3534   0.07341   0.06933  -0.0447   0.0033   1.0000
  14.750   1.3424   0.07896   0.07506  -0.0468   0.0033   1.0000
  15.000   1.3293   0.08516   0.08146  -0.0493   0.0033   1.0000
  15.250   1.3156   0.09167   0.08814  -0.0522   0.0033   1.0000
  15.500   1.3001   0.09887   0.09553  -0.0557   0.0033   1.0000
  15.750   1.2841   0.10647   0.10331  -0.0596   0.0033   1.0000
  16.000   1.2689   0.11420   0.11119  -0.0637   0.0033   1.0000
  16.250   1.2524   0.12260   0.11975  -0.0683   0.0033   1.0000
  16.500   1.2351   0.13161   0.12893  -0.0735   0.0033   1.0000
  16.750   1.2198   0.14039   0.13784  -0.0787   0.0033   1.0000
  17.000   1.2027   0.15020   0.14779  -0.0845   0.0033   1.0000
  17.250   1.1861   0.16041   0.15812  -0.0906   0.0034   1.0000
  17.500   1.1691   0.17136   0.16918  -0.0971   0.0034   1.0000
  17.750   1.1452   0.18589   0.18382  -0.1054   0.0035   1.0000
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