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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 200,000
Max Cl/Cd: 73.04 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa25-il-200000-n5.txt
Download as CSV file: xf-usa25-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 25 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3301   0.10502   0.10159  -0.0250   1.0000   0.0287
  -8.750  -0.3291   0.10297   0.09957  -0.0243   1.0000   0.0301
  -8.500  -0.3311   0.10067   0.09732  -0.0237   1.0000   0.0312
  -8.250  -0.3355   0.09836   0.09505  -0.0231   1.0000   0.0322
  -7.750  -0.3282   0.09070   0.08743  -0.0368   0.9895   0.0341
  -7.250  -0.2967   0.08120   0.07791  -0.0443   0.9800   0.0351
  -7.000  -0.2751   0.07900   0.07569  -0.0447   0.9767   0.0372
  -6.750  -0.2571   0.07542   0.07208  -0.0488   0.9706   0.0392
  -6.500  -0.2275   0.06949   0.06596  -0.0622   0.9622   0.0429
  -6.000  -0.1948   0.06265   0.05911  -0.0640   0.9496   0.0448
  -5.500  -0.1561   0.04992   0.04594  -0.0715   0.9284   0.0341
  -5.250  -0.1351   0.04526   0.04111  -0.0736   0.9198   0.0348
  -5.000  -0.1180   0.04414   0.03996  -0.0729   0.9090   0.0359
  -4.750  -0.0947   0.04138   0.03705  -0.0738   0.8997   0.0366
  -4.500  -0.0742   0.03304   0.02819  -0.0753   0.8901   0.0352
  -4.250  -0.0598   0.02434   0.01861  -0.0746   0.8794   0.0352
  -4.000  -0.0313   0.02205   0.01596  -0.0753   0.8692   0.0361
  -3.750   0.0028   0.01955   0.01294  -0.0768   0.8589   0.0365
  -3.500   0.0398   0.01781   0.01078  -0.0786   0.8459   0.0368
  -3.250   0.0792   0.01653   0.00917  -0.0809   0.8291   0.0372
  -3.000   0.1187   0.01556   0.00792  -0.0831   0.8071   0.0376
  -2.750   0.1548   0.01484   0.00694  -0.0846   0.7781   0.0383
  -2.500   0.1861   0.01435   0.00618  -0.0851   0.7372   0.0388
  -2.000   0.2332   0.01406   0.00516  -0.0827   0.6150   0.0404
  -1.750   0.2538   0.01404   0.00483  -0.0810   0.5720   0.0416
  -1.500   0.2756   0.01399   0.00456  -0.0796   0.5440   0.0425
  -1.250   0.2982   0.01393   0.00433  -0.0784   0.5246   0.0431
  -1.000   0.3215   0.01384   0.00411  -0.0774   0.5106   0.0441
  -0.750   0.3452   0.01377   0.00394  -0.0764   0.4994   0.0453
  -0.500   0.3689   0.01372   0.00381  -0.0755   0.4903   0.0475
  -0.250   0.3932   0.01364   0.00373  -0.0747   0.4823   0.0510
   0.000   0.4170   0.01361   0.00370  -0.0738   0.4758   0.0652
   0.250   0.4419   0.01360   0.00368  -0.0732   0.4704   0.0813
   0.500   0.4667   0.01363   0.00370  -0.0725   0.4653   0.0948
   0.750   0.4914   0.01371   0.00375  -0.0718   0.4609   0.1078
   1.000   0.5167   0.01377   0.00381  -0.0713   0.4565   0.1196
   1.250   0.5420   0.01383   0.00388  -0.0707   0.4521   0.1309
   1.500   0.5670   0.01391   0.00396  -0.0702   0.4482   0.1410
   1.750   0.5921   0.01402   0.00404  -0.0696   0.4450   0.1526
   2.000   0.6174   0.01409   0.00411  -0.0691   0.4417   0.1621
   2.250   0.6423   0.01414   0.00421  -0.0685   0.4381   0.1738
   2.500   0.6672   0.01422   0.00433  -0.0679   0.4343   0.1923
   2.750   0.6920   0.01432   0.00445  -0.0673   0.4308   0.2114
   3.000   0.7168   0.01443   0.00457  -0.0667   0.4268   0.2284
   3.250   0.7413   0.01447   0.00469  -0.0661   0.4223   0.2501
   3.500   0.7653   0.01450   0.00481  -0.0654   0.4177   0.2899
   4.000   0.8991   0.01385   0.00558  -0.0825   0.4042   1.0000
   4.250   0.9198   0.01402   0.00571  -0.0810   0.3992   1.0000
   4.500   0.9411   0.01421   0.00587  -0.0797   0.3953   1.0000
   4.750   0.9626   0.01435   0.00608  -0.0785   0.3916   1.0000
   5.000   0.9841   0.01451   0.00628  -0.0772   0.3879   1.0000
   5.250   1.0056   0.01470   0.00648  -0.0760   0.3842   1.0000
   5.500   1.0274   0.01492   0.00669  -0.0748   0.3810   1.0000
   5.750   1.0487   0.01507   0.00695  -0.0735   0.3767   1.0000
   6.000   1.0689   0.01521   0.00715  -0.0720   0.3706   1.0000
   6.250   1.0878   0.01533   0.00729  -0.0703   0.3622   1.0000
   6.500   1.1048   0.01542   0.00738  -0.0681   0.3502   1.0000
   6.750   1.1220   0.01550   0.00752  -0.0660   0.3353   1.0000
   7.000   1.1397   0.01562   0.00767  -0.0640   0.3166   1.0000
   7.250   1.1563   0.01583   0.00784  -0.0619   0.2942   1.0000
   7.500   1.1699   0.01620   0.00807  -0.0594   0.2635   1.0000
   7.750   1.1801   0.01684   0.00848  -0.0563   0.2247   1.0000
   8.000   1.1890   0.01769   0.00911  -0.0532   0.1902   1.0000
   8.250   1.1988   0.01850   0.00977  -0.0503   0.1636   1.0000
   8.500   1.2088   0.01922   0.01040  -0.0473   0.1399   1.0000
   8.750   1.2054   0.02066   0.01140  -0.0425   0.0790   1.0000
   9.000   1.2058   0.02193   0.01248  -0.0383   0.0497   1.0000
   9.250   1.2043   0.02335   0.01372  -0.0340   0.0217   1.0000
   9.500   1.2130   0.02423   0.01465  -0.0312   0.0190   1.0000
   9.750   1.2227   0.02507   0.01562  -0.0287   0.0179   1.0000
  10.000   1.2314   0.02598   0.01666  -0.0262   0.0171   1.0000
  10.250   1.2378   0.02707   0.01789  -0.0235   0.0162   1.0000
  10.500   1.2431   0.02826   0.01921  -0.0209   0.0156   1.0000
  10.750   1.2427   0.02989   0.02099  -0.0180   0.0145   1.0000
  11.000   1.2415   0.03167   0.02294  -0.0153   0.0139   1.0000
  11.250   1.2438   0.03330   0.02470  -0.0133   0.0137   1.0000
  11.500   1.2445   0.03518   0.02672  -0.0114   0.0134   1.0000
  11.750   1.2433   0.03736   0.02906  -0.0098   0.0132   1.0000
  12.000   1.2407   0.03983   0.03168  -0.0086   0.0129   1.0000
  12.250   1.2363   0.04269   0.03468  -0.0077   0.0127   1.0000
  12.500   1.2317   0.04579   0.03793  -0.0073   0.0126   1.0000
  12.750   1.2256   0.04932   0.04160  -0.0074   0.0124   1.0000
  13.000   1.2198   0.05301   0.04542  -0.0077   0.0122   1.0000
  13.250   1.2140   0.05684   0.04937  -0.0083   0.0121   1.0000
  13.500   1.2081   0.06079   0.05343  -0.0090   0.0119   1.0000
  13.750   1.2023   0.06475   0.05749  -0.0098   0.0117   1.0000
  14.000   1.1965   0.06872   0.06156  -0.0105   0.0113   1.0000
  14.250   1.1914   0.07261   0.06553  -0.0113   0.0111   1.0000
  14.500   1.1874   0.07633   0.06933  -0.0120   0.0110   1.0000
  14.750   1.1830   0.08008   0.07313  -0.0126   0.0107   1.0000
  15.000   1.1793   0.08362   0.07671  -0.0131   0.0103   1.0000
  15.250   1.1800   0.08646   0.07957  -0.0131   0.0102   1.0000
  15.500   1.1845   0.08850   0.08158  -0.0124   0.0100   1.0000
  15.750   1.1859   0.09169   0.08490  -0.0131   0.0098   1.0000
  16.000   1.1878   0.09477   0.08809  -0.0136   0.0097   1.0000
  16.250   1.1898   0.09786   0.09130  -0.0143   0.0095   1.0000
  16.500   1.1926   0.10077   0.09432  -0.0147   0.0095   1.0000
  16.750   1.1946   0.10389   0.09755  -0.0154   0.0094   1.0000
  17.000   1.1956   0.10721   0.10100  -0.0162   0.0093   1.0000
  17.250   1.1959   0.11074   0.10467  -0.0172   0.0092   1.0000
  17.500   1.1952   0.11451   0.10858  -0.0185   0.0091   1.0000
  17.750   1.1942   0.11838   0.11260  -0.0199   0.0090   1.0000
  18.000   1.1917   0.12257   0.11694  -0.0217   0.0090   1.0000
  18.250   1.1877   0.12717   0.12169  -0.0238   0.0089   1.0000
  18.500   1.1828   0.13204   0.12672  -0.0262   0.0088   1.0000
  18.750   1.1767   0.13728   0.13211  -0.0289   0.0088   1.0000
  19.000   1.1701   0.14274   0.13774  -0.0320   0.0087   1.0000
  19.250   1.1633   0.14838   0.14354  -0.0353   0.0086   1.0000
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