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USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 41 AIRFOIL (usa41-il)
Reynolds number: 200,000
Max Cl/Cd: 79.89 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa41-il-200000-n5.txt
Download as CSV file: xf-usa41-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3388   0.10212   0.09857  -0.0275   1.0000   0.0198
  -8.500  -0.3311   0.09836   0.09482  -0.0261   1.0000   0.0188
  -8.250  -0.3357   0.09620   0.09274  -0.0287   1.0000   0.0199
  -8.000  -0.3277   0.09280   0.08935  -0.0268   1.0000   0.0188
  -7.750  -0.3358   0.09065   0.08730  -0.0279   1.0000   0.0197
  -7.500  -0.3334   0.08791   0.08460  -0.0263   1.0000   0.0192
  -7.250  -0.3380   0.08569   0.08242  -0.0248   1.0000   0.0188
  -7.000  -0.3417   0.08337   0.08017  -0.0239   1.0000   0.0185
  -6.750  -0.3461   0.08112   0.07798  -0.0231   1.0000   0.0181
  -6.500  -0.3277   0.07657   0.07343  -0.0290   0.9956   0.0178
  -6.250  -0.2976   0.07076   0.06759  -0.0384   0.9882   0.0177
  -6.000  -0.2663   0.06485   0.06163  -0.0480   0.9803   0.0178
  -5.750  -0.2279   0.05716   0.05383  -0.0607   0.9723   0.0193
  -5.500  -0.1810   0.04731   0.04374  -0.0751   0.9661   0.0201
  -5.250  -0.1502   0.04143   0.03769  -0.0818   0.9587   0.0208
  -5.000  -0.1169   0.03895   0.03509  -0.0858   0.9541   0.0220
  -4.750  -0.0821   0.03480   0.03069  -0.0905   0.9477   0.0249
  -4.500  -0.0425   0.02544   0.02044  -0.0970   0.9416   0.0268
  -4.250  -0.0087   0.02165   0.01587  -0.0995   0.9360   0.0296
  -4.000   0.0212   0.01977   0.01368  -0.1006   0.9288   0.0313
  -3.750   0.0556   0.01821   0.01179  -0.1022   0.9238   0.0330
  -3.500   0.0849   0.01718   0.01049  -0.1026   0.9151   0.0355
  -3.250   0.1184   0.01600   0.00897  -0.1036   0.9087   0.0367
  -3.000   0.1479   0.01511   0.00783  -0.1037   0.8992   0.0374
  -2.750   0.1780   0.01436   0.00690  -0.1040   0.8899   0.0380
  -2.500   0.2085   0.01385   0.00623  -0.1043   0.8804   0.0393
  -2.250   0.2358   0.01307   0.00534  -0.1040   0.8686   0.0401
  -2.000   0.2631   0.01257   0.00477  -0.1037   0.8561   0.0403
  -1.750   0.2903   0.01214   0.00428  -0.1033   0.8428   0.0406
  -1.500   0.3172   0.01180   0.00384  -0.1028   0.8283   0.0412
  -1.250   0.3442   0.01152   0.00348  -0.1024   0.8128   0.0420
  -1.000   0.3712   0.01130   0.00316  -0.1019   0.7961   0.0433
  -0.750   0.3978   0.01113   0.00289  -0.1014   0.7779   0.0451
  -0.500   0.4244   0.01100   0.00265  -0.1008   0.7587   0.0474
  -0.250   0.4509   0.01092   0.00245  -0.1002   0.7387   0.0507
   0.000   0.4769   0.01080   0.00232  -0.0996   0.7182   0.0633
   0.250   0.5023   0.01063   0.00240  -0.0991   0.6973   0.1635
   0.500   0.5282   0.01072   0.00240  -0.0984   0.6764   0.1892
   0.750   0.5539   0.01079   0.00239  -0.0978   0.6554   0.2015
   1.000   0.5794   0.01087   0.00238  -0.0972   0.6350   0.2158
   1.500   0.6302   0.01099   0.00242  -0.0960   0.5966   0.2478
   1.750   0.6554   0.01099   0.00249  -0.0955   0.5793   0.2875
   2.000   0.6947   0.00979   0.00264  -0.0982   0.5620   1.0000
   2.250   0.7202   0.01000   0.00274  -0.0976   0.5470   1.0000
   2.500   0.7457   0.01021   0.00287  -0.0970   0.5328   1.0000
   2.750   0.7712   0.01042   0.00300  -0.0965   0.5193   1.0000
   3.000   0.7967   0.01064   0.00316  -0.0959   0.5063   1.0000
   3.250   0.8221   0.01085   0.00335  -0.0954   0.4937   1.0000
   3.500   0.8475   0.01108   0.00353  -0.0948   0.4812   1.0000
   3.750   0.8727   0.01131   0.00374  -0.0943   0.4686   1.0000
   4.000   0.8978   0.01155   0.00397  -0.0937   0.4561   1.0000
   4.500   0.9479   0.01204   0.00445  -0.0925   0.4308   1.0000
   4.750   0.9727   0.01229   0.00472  -0.0919   0.4173   1.0000
   5.000   0.9974   0.01255   0.00502  -0.0913   0.4038   1.0000
   5.250   1.0221   0.01282   0.00533  -0.0907   0.3921   1.0000
   5.500   1.0465   0.01310   0.00566  -0.0900   0.3790   1.0000
   5.750   1.0689   0.01347   0.00596  -0.0890   0.3508   1.0000
   6.000   1.0894   0.01398   0.00632  -0.0878   0.3086   1.0000
   6.250   1.1101   0.01454   0.00674  -0.0866   0.2679   1.0000
   6.500   1.1274   0.01548   0.00732  -0.0851   0.1982   1.0000
   6.750   1.1372   0.01738   0.00849  -0.0829   0.0859   1.0000
   7.000   1.1501   0.01895   0.00972  -0.0808   0.0336   1.0000
   7.250   1.1680   0.01993   0.01073  -0.0792   0.0241   1.0000
   7.500   1.1851   0.02095   0.01191  -0.0775   0.0205   1.0000
   7.750   1.2028   0.02185   0.01297  -0.0759   0.0185   1.0000
   8.000   1.2192   0.02279   0.01405  -0.0742   0.0165   1.0000
   8.250   1.2335   0.02388   0.01524  -0.0723   0.0148   1.0000
   8.500   1.2432   0.02531   0.01680  -0.0697   0.0138   1.0000
   8.750   1.2478   0.02713   0.01875  -0.0665   0.0130   1.0000
   9.000   1.2532   0.02879   0.02052  -0.0634   0.0125   1.0000
   9.250   1.2624   0.03004   0.02189  -0.0608   0.0120   1.0000
   9.500   1.2711   0.03141   0.02343  -0.0583   0.0114   1.0000
   9.750   1.2798   0.03276   0.02490  -0.0560   0.0107   1.0000
  10.000   1.2877   0.03429   0.02655  -0.0538   0.0101   1.0000
  10.250   1.2948   0.03605   0.02843  -0.0517   0.0097   1.0000
  10.500   1.3017   0.03795   0.03047  -0.0497   0.0094   1.0000
  10.750   1.3079   0.03993   0.03258  -0.0478   0.0091   1.0000
  11.000   1.3135   0.04213   0.03493  -0.0460   0.0089   1.0000
  11.250   1.3174   0.04465   0.03759  -0.0444   0.0087   1.0000
  11.500   1.3201   0.04750   0.04062  -0.0428   0.0085   1.0000
  11.750   1.3200   0.05095   0.04429  -0.0413   0.0084   1.0000
  12.000   1.3169   0.05454   0.04812  -0.0400   0.0083   1.0000
  12.250   1.3112   0.05788   0.05172  -0.0390   0.0082   1.0000
  12.500   1.3035   0.06146   0.05557  -0.0386   0.0081   1.0000
  12.750   1.2941   0.06556   0.05996  -0.0387   0.0080   1.0000
  13.000   1.2838   0.06988   0.06453  -0.0394   0.0079   1.0000
  13.250   1.2714   0.07486   0.06976  -0.0407   0.0078   1.0000
  13.500   1.2576   0.08037   0.07550  -0.0426   0.0077   1.0000
  13.750   1.2432   0.08628   0.08163  -0.0451   0.0077   1.0000
  14.000   1.2277   0.09275   0.08831  -0.0483   0.0076   1.0000
  14.250   1.2121   0.09964   0.09538  -0.0519   0.0077   1.0000
  14.500   1.1955   0.10716   0.10309  -0.0561   0.0077   1.0000
  14.750   1.1795   0.11498   0.11108  -0.0608   0.0077   1.0000
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