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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.86 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e639-il-1000000.txt
Download as CSV file: xf-e639-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 639 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1876   0.08937   0.08680  -0.0551   0.7312   0.0108
  -9.250  -0.1832   0.08699   0.08433  -0.0556   0.7068   0.0113
  -9.000  -0.1813   0.08384   0.08113  -0.0567   0.6892   0.0110
  -8.750  -0.1782   0.08113   0.07836  -0.0576   0.6721   0.0114
  -8.500  -0.1768   0.07810   0.07529  -0.0588   0.6582   0.0118
  -8.250  -0.1765   0.07498   0.07215  -0.0600   0.6458   0.0122
  -8.000  -0.1804   0.07146   0.06861  -0.0619   0.6349   0.0126
  -7.750  -0.1983   0.06704   0.06418  -0.0649   0.6264   0.0130
  -7.500  -0.1997   0.06299   0.06008  -0.0667   0.6174   0.0130
  -7.250  -0.1964   0.05935   0.05635  -0.0679   0.6077   0.0131
  -7.000  -0.1915   0.05546   0.05237  -0.0686   0.5992   0.0131
  -6.750  -0.1848   0.05166   0.04844  -0.0687   0.5906   0.0131
  -6.500  -0.1762   0.04768   0.04432  -0.0685   0.5825   0.0132
  -6.250  -0.1770   0.04306   0.03955  -0.0677   0.5748   0.0135
  -6.000  -0.1633   0.04110   0.03750  -0.0672   0.5658   0.0137
  -5.750  -0.1483   0.03901   0.03528  -0.0665   0.5565   0.0139
  -5.500  -0.1322   0.03690   0.03303  -0.0657   0.5474   0.0142
  -5.250  -0.1152   0.03466   0.03064  -0.0648   0.5397   0.0148
  -5.000  -0.0935   0.03068   0.02627  -0.0624   0.5329   0.0167
  -4.750  -0.0857   0.02555   0.02069  -0.0596   0.5273   0.0170
  -4.500  -0.0665   0.02391   0.01895  -0.0587   0.5196   0.0174
  -4.250  -0.0452   0.02281   0.01772  -0.0579   0.5117   0.0177
  -4.000  -0.0229   0.02170   0.01648  -0.0571   0.5041   0.0181
  -3.750  -0.0003   0.02054   0.01513  -0.0562   0.4966   0.0188
  -3.500   0.0270   0.02025   0.01455  -0.0550   0.4894   0.0211
  -3.250   0.0449   0.01700   0.01097  -0.0533   0.4834   0.0222
  -3.000   0.0699   0.01624   0.01014  -0.0528   0.4773   0.0228
  -2.750   0.0953   0.01561   0.00940  -0.0523   0.4709   0.0242
  -2.500   0.1236   0.01642   0.01004  -0.0518   0.4647   0.0266
  -2.250   0.1478   0.01261   0.00589  -0.0503   0.4598   0.0200
  -2.000   0.1737   0.01178   0.00493  -0.0496   0.4538   0.0195
  -1.750   0.2002   0.01136   0.00445  -0.0492   0.4488   0.0199
  -1.500   0.2259   0.01083   0.00386  -0.0485   0.4438   0.0198
  -1.250   0.2513   0.01046   0.00343  -0.0479   0.4389   0.0200
  -1.000   0.2772   0.01020   0.00312  -0.0473   0.4345   0.0205
  -0.750   0.3035   0.01000   0.00290  -0.0469   0.4298   0.0210
  -0.500   0.3292   0.00981   0.00265  -0.0463   0.4250   0.0213
  -0.250   0.3544   0.00955   0.00234  -0.0457   0.4207   0.0219
   0.000   0.3808   0.00938   0.00216  -0.0453   0.4172   0.0232
   0.250   0.4075   0.00929   0.00205  -0.0450   0.4132   0.0246
   0.500   0.4340   0.00924   0.00196  -0.0446   0.4090   0.0260
   0.750   0.4607   0.00920   0.00188  -0.0443   0.4052   0.0286
   1.000   0.4875   0.00909   0.00185  -0.0440   0.4017   0.0513
   1.250   0.4877   0.00700   0.00188  -0.0390   0.3992   0.8014
   1.500   0.5266   0.00695   0.00220  -0.0407   0.3952   0.9649
   1.750   0.5800   0.00724   0.00240  -0.0460   0.3908   0.9773
   2.000   0.6283   0.00742   0.00253  -0.0502   0.3873   0.9846
   2.250   0.6951   0.00759   0.00262  -0.0585   0.3826   0.9900
   2.500   0.7281   0.00769   0.00266  -0.0597   0.3791   0.9921
   2.750   0.7584   0.00779   0.00272  -0.0604   0.3758   0.9940
   3.000   0.7924   0.00780   0.00273  -0.0618   0.3729   0.9950
   3.250   0.8258   0.00784   0.00274  -0.0632   0.3698   0.9962
   3.500   0.8587   0.00790   0.00277  -0.0644   0.3666   0.9975
   3.750   0.8910   0.00801   0.00284  -0.0656   0.3631   0.9989
   4.000   0.9237   0.00807   0.00289  -0.0668   0.3604   1.0000
   4.250   0.9475   0.00811   0.00294  -0.0661   0.3578   1.0000
   4.500   0.9707   0.00818   0.00301  -0.0653   0.3552   1.0000
   4.750   0.9936   0.00827   0.00309  -0.0644   0.3524   1.0000
   5.000   1.0159   0.00839   0.00320  -0.0635   0.3494   1.0000
   5.250   1.0383   0.00852   0.00332  -0.0625   0.3465   1.0000
   5.500   1.0616   0.00859   0.00342  -0.0617   0.3442   1.0000
   5.750   1.0846   0.00867   0.00352  -0.0609   0.3416   1.0000
   6.000   1.1073   0.00877   0.00362  -0.0600   0.3385   1.0000
   6.250   1.1292   0.00892   0.00376  -0.0589   0.3350   1.0000
   6.500   1.1512   0.00907   0.00392  -0.0579   0.3317   1.0000
   6.750   1.1744   0.00915   0.00403  -0.0571   0.3290   1.0000
   7.000   1.1973   0.00925   0.00415  -0.0563   0.3255   1.0000
   7.250   1.2192   0.00939   0.00430  -0.0553   0.3217   1.0000
   7.500   1.2404   0.00958   0.00448  -0.0542   0.3176   1.0000
   7.750   1.2637   0.00966   0.00461  -0.0534   0.3146   1.0000
   8.000   1.2862   0.00978   0.00476  -0.0526   0.3110   1.0000
   8.250   1.3077   0.00995   0.00494  -0.0515   0.3071   1.0000
   8.500   1.3287   0.01015   0.00514  -0.0504   0.3030   1.0000
   8.750   1.3516   0.01025   0.00529  -0.0497   0.2989   1.0000
   9.000   1.3730   0.01042   0.00548  -0.0487   0.2935   1.0000
   9.250   1.3937   0.01063   0.00570  -0.0475   0.2886   1.0000
   9.500   1.4159   0.01077   0.00588  -0.0467   0.2827   1.0000
   9.750   1.4354   0.01104   0.00612  -0.0454   0.2759   1.0000
  10.000   1.4568   0.01122   0.00634  -0.0445   0.2684   1.0000
  10.250   1.4757   0.01152   0.00662  -0.0432   0.2581   1.0000
  10.500   1.4933   0.01187   0.00694  -0.0416   0.2459   1.0000
  10.750   1.5098   0.01227   0.00730  -0.0399   0.2336   1.0000
  11.000   1.5253   0.01272   0.00772  -0.0381   0.2203   1.0000
  11.250   1.5386   0.01324   0.00819  -0.0360   0.2049   1.0000
  11.500   1.5486   0.01389   0.00877  -0.0333   0.1867   1.0000
  11.750   1.5496   0.01471   0.00947  -0.0291   0.1676   1.0000
  12.000   1.5504   0.01555   0.01024  -0.0251   0.1506   1.0000
  12.250   1.5507   0.01652   0.01114  -0.0213   0.1343   1.0000
  12.500   1.5517   0.01756   0.01214  -0.0180   0.1213   1.0000
  12.750   1.5514   0.01878   0.01334  -0.0149   0.1094   1.0000
  13.000   1.5490   0.02029   0.01482  -0.0122   0.0979   1.0000
  13.250   1.5459   0.02212   0.01664  -0.0101   0.0876   1.0000
  13.500   1.5412   0.02436   0.01887  -0.0085   0.0780   1.0000
  13.750   1.5357   0.02696   0.02147  -0.0075   0.0691   1.0000
  14.000   1.5315   0.02968   0.02422  -0.0070   0.0620   1.0000
  14.250   1.5241   0.03287   0.02743  -0.0066   0.0557   1.0000
  14.500   1.5121   0.03664   0.03123  -0.0065   0.0491   1.0000
  14.750   1.5053   0.03997   0.03463  -0.0066   0.0450   1.0000
  15.000   1.4937   0.04385   0.03856  -0.0067   0.0411   1.0000
  15.250   1.4800   0.04801   0.04277  -0.0069   0.0364   1.0000
  15.500   1.4600   0.05299   0.04778  -0.0073   0.0310   1.0000
  15.750   1.4487   0.05712   0.05198  -0.0078   0.0279   1.0000
  16.000   1.4311   0.06211   0.05700  -0.0085   0.0236   1.0000
  16.250   1.4160   0.06688   0.06182  -0.0093   0.0201   1.0000
  16.500   1.3994   0.07196   0.06693  -0.0102   0.0159   1.0000
  16.750   1.3820   0.07722   0.07222  -0.0112   0.0119   1.0000
  17.000   1.3646   0.08261   0.07765  -0.0124   0.0084   1.0000
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