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USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 41 AIRFOIL (usa41-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.82 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa41-il-1000000-n5.txt
Download as CSV file: xf-usa41-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3666   0.09841   0.09678  -0.0238   1.0000   0.0042
  -9.000  -0.3697   0.09372   0.09212  -0.0250   1.0000   0.0046
  -8.000  -0.3888   0.01635   0.01308  -0.1040   0.9624   0.0061
  -7.750  -0.3574   0.01438   0.01077  -0.1059   0.9537   0.0065
  -7.500  -0.3253   0.01312   0.00924  -0.1074   0.9425   0.0068
  -7.250  -0.2945   0.01229   0.00823  -0.1083   0.9300   0.0075
  -7.000  -0.2668   0.01157   0.00735  -0.1085   0.9193   0.0083
  -6.500  -0.2138   0.01042   0.00588  -0.1082   0.9018   0.0105
  -6.250  -0.1862   0.01039   0.00585  -0.1080   0.8940   0.0120
  -6.000  -0.1592   0.01026   0.00566  -0.1077   0.8861   0.0133
  -5.750  -0.1323   0.01010   0.00543  -0.1075   0.8784   0.0144
  -5.500  -0.1045   0.01032   0.00566  -0.1072   0.8699   0.0152
  -5.250  -0.0769   0.01049   0.00581  -0.1070   0.8615   0.0162
  -5.000  -0.0499   0.01048   0.00572  -0.1067   0.8523   0.0175
  -4.750  -0.0231   0.01034   0.00549  -0.1064   0.8417   0.0187
  -4.500   0.0038   0.01027   0.00533  -0.1060   0.8302   0.0194
  -4.250   0.0307   0.01037   0.00535  -0.1057   0.8162   0.0199
  -4.000   0.0572   0.01036   0.00524  -0.1053   0.7995   0.0201
  -3.750   0.0815   0.00947   0.00418  -0.1047   0.7805   0.0216
  -3.500   0.1074   0.00930   0.00391  -0.1042   0.7603   0.0223
  -3.250   0.1332   0.00915   0.00365  -0.1037   0.7394   0.0229
  -3.000   0.1592   0.00902   0.00340  -0.1032   0.7193   0.0237
  -2.750   0.1850   0.00881   0.00307  -0.1027   0.6989   0.0240
  -2.250   0.2369   0.00847   0.00249  -0.1017   0.6578   0.0246
  -2.000   0.2627   0.00833   0.00223  -0.1012   0.6351   0.0247
  -1.750   0.2889   0.00823   0.00202  -0.1007   0.6138   0.0250
  -1.500   0.3148   0.00817   0.00184  -0.1002   0.5912   0.0254
  -1.250   0.3410   0.00808   0.00164  -0.0998   0.5718   0.0254
  -1.000   0.3674   0.00801   0.00148  -0.0994   0.5548   0.0255
  -0.750   0.3939   0.00796   0.00134  -0.0990   0.5395   0.0257
  -0.500   0.4204   0.00792   0.00123  -0.0987   0.5259   0.0261
  -0.250   0.4471   0.00789   0.00115  -0.0983   0.5142   0.0267
   0.250   0.5007   0.00790   0.00106  -0.0977   0.4914   0.0281
   0.500   0.5276   0.00792   0.00105  -0.0975   0.4816   0.0286
   0.750   0.5543   0.00793   0.00102  -0.0972   0.4718   0.0299
   1.000   0.5812   0.00795   0.00100  -0.0969   0.4612   0.0310
   1.250   0.6080   0.00799   0.00100  -0.0966   0.4514   0.0323
   1.500   0.6347   0.00804   0.00102  -0.0963   0.4414   0.0337
   1.750   0.6614   0.00810   0.00106  -0.0960   0.4306   0.0354
   2.000   0.6880   0.00815   0.00111  -0.0957   0.4190   0.0387
   2.250   0.7138   0.00803   0.00123  -0.0954   0.4058   0.1648
   2.500   0.7400   0.00814   0.00133  -0.0950   0.3900   0.1804
   2.750   0.7662   0.00826   0.00142  -0.0947   0.3757   0.1904
   3.000   0.7925   0.00836   0.00152  -0.0944   0.3641   0.1986
   3.500   0.8452   0.00855   0.00173  -0.0937   0.3450   0.2141
   3.750   0.8714   0.00863   0.00185  -0.0934   0.3350   0.2355
   4.000   0.8926   0.00800   0.00214  -0.0925   0.3241   0.6844
   4.250   0.9359   0.00762   0.00234  -0.0961   0.3097   1.0000
   4.500   0.9598   0.00797   0.00253  -0.0954   0.2762   1.0000
   4.750   0.9840   0.00830   0.00273  -0.0948   0.2492   1.0000
   5.000   1.0069   0.00876   0.00301  -0.0940   0.2111   1.0000
   5.250   1.0285   0.00937   0.00338  -0.0930   0.1629   1.0000
   5.500   1.0466   0.01037   0.00397  -0.0915   0.0874   1.0000
   6.000   1.0895   0.01165   0.00492  -0.0894   0.0215   1.0000
   6.250   1.1131   0.01204   0.00527  -0.0886   0.0147   1.0000
   6.500   1.1371   0.01235   0.00561  -0.0880   0.0118   1.0000
   6.750   1.1608   0.01270   0.00597  -0.0873   0.0102   1.0000
   7.000   1.1836   0.01314   0.00643  -0.0864   0.0083   1.0000
   7.250   1.2071   0.01348   0.00680  -0.0857   0.0076   1.0000
   7.500   1.2301   0.01385   0.00720  -0.0849   0.0069   1.0000
   7.750   1.2523   0.01429   0.00767  -0.0840   0.0061   1.0000
   8.000   1.2734   0.01485   0.00827  -0.0829   0.0055   1.0000
   8.250   1.2955   0.01528   0.00875  -0.0820   0.0052   1.0000
   8.500   1.3168   0.01576   0.00929  -0.0810   0.0049   1.0000
   8.750   1.3375   0.01628   0.00987  -0.0799   0.0046   1.0000
   9.000   1.3579   0.01680   0.01043  -0.0788   0.0043   1.0000
   9.250   1.3778   0.01733   0.01099  -0.0776   0.0040   1.0000
   9.500   1.3951   0.01808   0.01180  -0.0760   0.0037   1.0000
   9.750   1.4124   0.01877   0.01257  -0.0745   0.0035   1.0000
  10.000   1.4295   0.01944   0.01332  -0.0729   0.0034   1.0000
  10.250   1.4456   0.02014   0.01409  -0.0712   0.0032   1.0000
  10.500   1.4601   0.02091   0.01497  -0.0693   0.0031   1.0000
  10.750   1.4727   0.02168   0.01581  -0.0670   0.0030   1.0000
  11.000   1.4811   0.02253   0.01675  -0.0641   0.0029   1.0000
  11.250   1.4907   0.02333   0.01762  -0.0615   0.0028   1.0000
  11.500   1.4988   0.02423   0.01860  -0.0588   0.0027   1.0000
  11.750   1.5039   0.02538   0.01985  -0.0559   0.0026   1.0000
  12.000   1.5126   0.02634   0.02088  -0.0538   0.0025   1.0000
  12.250   1.5166   0.02768   0.02232  -0.0513   0.0025   1.0000
  12.500   1.5215   0.02905   0.02377  -0.0492   0.0024   1.0000
  12.750   1.5226   0.03082   0.02565  -0.0470   0.0024   1.0000
  13.000   1.5238   0.03270   0.02765  -0.0452   0.0023   1.0000
  13.250   1.5199   0.03521   0.03029  -0.0434   0.0022   1.0000
  13.500   1.5101   0.03852   0.03376  -0.0419   0.0022   1.0000
  13.750   1.5090   0.04117   0.03653  -0.0411   0.0021   1.0000
  14.000   1.5080   0.04394   0.03944  -0.0407   0.0021   1.0000
  14.250   1.5034   0.04735   0.04297  -0.0406   0.0021   1.0000
  14.500   1.4984   0.05097   0.04673  -0.0408   0.0021   1.0000
  14.750   1.4966   0.05432   0.05020  -0.0413   0.0021   1.0000
  15.000   1.4880   0.05880   0.05483  -0.0423   0.0020   1.0000
  15.250   1.4791   0.06347   0.05963  -0.0435   0.0020   1.0000
  15.500   1.4708   0.06826   0.06456  -0.0450   0.0020   1.0000
  15.750   1.4598   0.07365   0.07009  -0.0468   0.0020   1.0000
  16.000   1.4465   0.07955   0.07613  -0.0490   0.0020   1.0000
  16.250   1.4383   0.08482   0.08153  -0.0511   0.0020   1.0000
  16.500   1.4260   0.09097   0.08781  -0.0537   0.0019   1.0000
  16.750   1.4141   0.09719   0.09415  -0.0565   0.0019   1.0000
  17.000   1.4021   0.10367   0.10075  -0.0595   0.0019   1.0000
  17.250   1.3833   0.11166   0.10890  -0.0634   0.0019   1.0000
  17.500   1.3697   0.11883   0.11619  -0.0670   0.0019   1.0000
  17.750   1.3536   0.12678   0.12429  -0.0712   0.0019   1.0000
  18.000   1.3372   0.13503   0.13267  -0.0757   0.0019   1.0000
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