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USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 25 AIRFOIL (usa25-il)
Reynolds number: 100,000
Max Cl/Cd: 52.57 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa25-il-100000.txt
Download as CSV file: xf-usa25-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3412   0.09638   0.09193  -0.0191   1.0000   0.0845
  -7.000  -0.3532   0.09496   0.09060  -0.0175   1.0000   0.0859
  -6.750  -0.3636   0.09379   0.08949  -0.0178   1.0000   0.0878
  -6.500  -0.3748   0.09407   0.08978  -0.0205   1.0000   0.0890
  -6.250  -0.3774   0.09421   0.08982  -0.0236   1.0000   0.0895
  -6.000  -0.3756   0.08750   0.08327  -0.0194   1.0000   0.0903
  -5.750  -0.3729   0.08363   0.07945  -0.0161   1.0000   0.0915
  -5.500  -0.3706   0.08079   0.07665  -0.0140   1.0000   0.0930
  -5.250  -0.3677   0.07833   0.07420  -0.0129   1.0000   0.0949
  -5.000  -0.3633   0.07599   0.07187  -0.0126   1.0000   0.0979
  -4.500  -0.3417   0.07179   0.06744  -0.0173   1.0000   0.1048
  -4.250  -0.3248   0.06759   0.06330  -0.0174   0.9965   0.1069
  -4.000  -0.2858   0.06379   0.05940  -0.0228   0.9879   0.1118
  -3.750  -0.2309   0.06076   0.05599  -0.0327   0.9774   0.1195
  -3.500  -0.1975   0.05631   0.05157  -0.0359   0.9699   0.1231
  -3.250  -0.1472   0.05404   0.04894  -0.0427   0.9582   0.1345
  -3.000  -0.1169   0.05000   0.04493  -0.0448   0.9474   0.1381
  -2.750  -0.0666   0.04805   0.04259  -0.0504   0.9352   0.1495
  -2.500  -0.0277   0.04391   0.03848  -0.0537   0.9265   0.1541
  -2.250   0.0176   0.04150   0.03577  -0.0576   0.9140   0.1656
  -2.000   0.0585   0.03924   0.03331  -0.0603   0.9002   0.1798
  -1.500   0.1502   0.02967   0.02261  -0.0647   0.8740   0.1067
  -1.250   0.1957   0.02614   0.01858  -0.0667   0.8598   0.1000
  -1.000   0.2458   0.02309   0.01504  -0.0695   0.8432   0.1001
  -0.750   0.2961   0.02103   0.01267  -0.0726   0.8183   0.1078
  -0.500   0.3486   0.01924   0.01046  -0.0761   0.7859   0.1194
  -0.250   0.3947   0.01826   0.00924  -0.0787   0.7485   0.1466
   0.000   0.4277   0.01805   0.00879  -0.0792   0.7128   0.1797
   0.250   0.4582   0.01812   0.00867  -0.0796   0.6869   0.2053
   0.500   0.4869   0.01806   0.00842  -0.0796   0.6662   0.2205
   0.750   0.5150   0.01806   0.00828  -0.0796   0.6502   0.2392
   1.000   0.5437   0.01798   0.00811  -0.0797   0.6369   0.2556
   1.250   0.5745   0.01792   0.00790  -0.0800   0.6255   0.2669
   1.500   0.6047   0.01781   0.00778  -0.0804   0.6150   0.2803
   1.750   0.6322   0.01774   0.00771  -0.0802   0.6063   0.2977
   2.000   0.6569   0.01767   0.00762  -0.0796   0.5984   0.3247
   2.250   0.6780   0.01743   0.00764  -0.0784   0.5910   0.3834
   2.500   0.7975   0.01686   0.00797  -0.0969   0.5798   1.0000
   2.750   0.8188   0.01723   0.00830  -0.0956   0.5727   1.0000
   3.000   0.8432   0.01765   0.00857  -0.0950   0.5669   1.0000
   3.250   0.8640   0.01807   0.00901  -0.0937   0.5607   1.0000
   3.500   0.8862   0.01849   0.00937  -0.0926   0.5538   1.0000
   3.750   0.9075   0.01892   0.00976  -0.0913   0.5462   1.0000
   4.000   0.9289   0.01930   0.01008  -0.0900   0.5375   1.0000
   4.250   0.9485   0.01972   0.01053  -0.0884   0.5289   1.0000
   4.500   0.9714   0.02013   0.01087  -0.0874   0.5212   1.0000
   4.750   0.9907   0.02063   0.01144  -0.0859   0.5145   1.0000
   5.000   1.0123   0.02110   0.01194  -0.0847   0.5077   1.0000
   5.250   1.0338   0.02163   0.01249  -0.0835   0.5013   1.0000
   5.500   1.0530   0.02213   0.01309  -0.0820   0.4939   1.0000
   5.750   1.0770   0.02268   0.01360  -0.0812   0.4876   1.0000
   6.000   1.0934   0.02325   0.01437  -0.0792   0.4800   1.0000
   6.250   1.1194   0.02377   0.01483  -0.0788   0.4732   1.0000
   6.500   1.1332   0.02436   0.01564  -0.0763   0.4644   1.0000
   6.750   1.1580   0.02487   0.01611  -0.0757   0.4568   1.0000
   7.000   1.1730   0.02544   0.01687  -0.0734   0.4472   1.0000
   7.250   1.1927   0.02594   0.01746  -0.0718   0.4376   1.0000
   7.500   1.2152   0.02603   0.01750  -0.0705   0.4250   1.0000
   7.750   1.2350   0.02600   0.01745  -0.0687   0.4114   1.0000
   8.000   1.2490   0.02616   0.01776  -0.0660   0.3984   1.0000
   8.250   1.2643   0.02611   0.01780  -0.0635   0.3844   1.0000
   8.500   1.2786   0.02583   0.01758  -0.0607   0.3696   1.0000
   8.750   1.2920   0.02565   0.01749  -0.0578   0.3556   1.0000
   9.000   1.3053   0.02558   0.01753  -0.0550   0.3425   1.0000
   9.250   1.3176   0.02553   0.01761  -0.0520   0.3292   1.0000
   9.500   1.3260   0.02538   0.01760  -0.0484   0.3123   1.0000
   9.750   1.3342   0.02538   0.01768  -0.0448   0.2946   1.0000
  10.000   1.3417   0.02559   0.01791  -0.0412   0.2773   1.0000
  10.250   1.3466   0.02603   0.01841  -0.0374   0.2578   1.0000
  10.500   1.3460   0.02667   0.01896  -0.0328   0.2358   1.0000
  10.750   1.3451   0.02763   0.01988  -0.0286   0.2128   1.0000
  11.000   1.3409   0.02894   0.02111  -0.0243   0.1893   1.0000
  11.250   1.3321   0.03071   0.02278  -0.0199   0.1605   1.0000
  11.500   1.3192   0.03301   0.02498  -0.0158   0.1191   1.0000
  11.750   1.2970   0.03624   0.02787  -0.0118   0.0859   1.0000
  12.000   1.2801   0.03948   0.03105  -0.0091   0.0745   1.0000
  12.250   1.2626   0.04320   0.03479  -0.0072   0.0662   1.0000
  12.500   1.2444   0.04745   0.03907  -0.0062   0.0619   1.0000
  12.750   1.2330   0.05139   0.04314  -0.0059   0.0579   1.0000
  13.000   1.2205   0.05580   0.04766  -0.0063   0.0548   1.0000
  13.250   1.2070   0.06055   0.05249  -0.0070   0.0527   1.0000
  13.500   1.1942   0.06528   0.05728  -0.0078   0.0511   1.0000
  13.750   1.1890   0.06904   0.06116  -0.0081   0.0494   1.0000
  14.000   1.1852   0.07257   0.06481  -0.0083   0.0475   1.0000
  14.250   1.1844   0.07562   0.06794  -0.0082   0.0462   1.0000
  14.500   1.1849   0.07845   0.07082  -0.0079   0.0444   1.0000
  14.750   1.1897   0.08054   0.07293  -0.0072   0.0432   1.0000
  15.000   1.2084   0.08022   0.07244  -0.0038   0.0413   1.0000
  15.250   1.2187   0.08204   0.07445  -0.0028   0.0404   1.0000
  15.500   1.2250   0.08455   0.07713  -0.0023   0.0394   1.0000
  15.750   1.2287   0.08750   0.08026  -0.0023   0.0384   1.0000
  16.000   1.2319   0.09064   0.08357  -0.0024   0.0376   1.0000
  16.250   1.2311   0.09441   0.08752  -0.0031   0.0369   1.0000
  16.500   1.2302   0.09836   0.09168  -0.0037   0.0368   1.0000
  16.750   1.2231   0.10332   0.09687  -0.0053   0.0368   1.0000
  17.000   1.2115   0.10911   0.10290  -0.0077   0.0369   1.0000
  17.250   1.1959   0.11573   0.10976  -0.0110   0.0371   1.0000
  17.500   1.1760   0.12336   0.11764  -0.0151   0.0375   1.0000
  17.750   1.1530   0.13195   0.12644  -0.0202   0.0379   1.0000
  18.000   1.1269   0.14178   0.13648  -0.0264   0.0385   1.0000
  18.250   1.0968   0.15335   0.14821  -0.0339   0.0393   1.0000
  18.500   1.0676   0.16581   0.16077  -0.0416   0.0403   1.0000
  18.750   1.0480   0.17658   0.17153  -0.0476   0.0411   1.0000
  19.000   0.9806   0.21298   0.20770  -0.0664   0.0591   1.0000
  19.250   0.9905   0.21640   0.21115  -0.0668   0.0610   1.0000
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