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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 500,000
Max Cl/Cd: 102.31 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e639-il-500000-n5.txt
Download as CSV file: xf-e639-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2122   0.10432   0.10108  -0.0466   0.7333   0.0108
 -10.250  -0.2081   0.10135   0.09803  -0.0477   0.7133   0.0126
  -9.750  -0.2045   0.09450   0.09107  -0.0508   0.6809   0.0129
  -8.750  -0.1561   0.07085   0.06738  -0.0510   0.6029   0.0131
  -8.500  -0.1569   0.06685   0.06336  -0.0525   0.5955   0.0131
  -8.250  -0.1608   0.06247   0.05899  -0.0542   0.5891   0.0132
  -7.750  -0.2144   0.06621   0.06256  -0.0639   0.5956   0.0131
  -7.250  -0.2103   0.05979   0.05602  -0.0651   0.5789   0.0129
  -7.000  -0.2030   0.05775   0.05391  -0.0649   0.5697   0.0125
  -6.750  -0.1980   0.05408   0.05014  -0.0655   0.5622   0.0123
  -6.500  -0.1914   0.05000   0.04591  -0.0658   0.5555   0.0123
  -6.250  -0.1816   0.04660   0.04236  -0.0656   0.5480   0.0121
  -6.000  -0.1710   0.04259   0.03814  -0.0649   0.5419   0.0123
  -5.750  -0.1584   0.03891   0.03425  -0.0640   0.5354   0.0123
  -5.500  -0.1448   0.03510   0.03016  -0.0625   0.5294   0.0125
  -5.250  -0.1311   0.02995   0.02459  -0.0602   0.5241   0.0130
  -5.000  -0.1168   0.02600   0.02022  -0.0579   0.5180   0.0130
  -4.750  -0.1010   0.02264   0.01637  -0.0558   0.5121   0.0132
  -4.500  -0.0810   0.02078   0.01423  -0.0546   0.5049   0.0135
  -4.250  -0.0584   0.01959   0.01283  -0.0537   0.4977   0.0137
  -4.000  -0.0348   0.01846   0.01148  -0.0528   0.4907   0.0139
  -3.500   0.0147   0.01680   0.00947  -0.0515   0.4784   0.0145
  -3.250   0.0402   0.01610   0.00860  -0.0509   0.4722   0.0151
  -3.000   0.0659   0.01531   0.00763  -0.0503   0.4665   0.0154
  -2.750   0.0919   0.01456   0.00671  -0.0497   0.4605   0.0156
  -2.500   0.1177   0.01396   0.00597  -0.0491   0.4548   0.0158
  -2.250   0.1438   0.01345   0.00537  -0.0486   0.4499   0.0161
  -2.000   0.1697   0.01306   0.00488  -0.0481   0.4449   0.0165
  -1.750   0.1955   0.01274   0.00448  -0.0475   0.4402   0.0168
  -1.500   0.2214   0.01248   0.00416  -0.0470   0.4357   0.0171
  -1.250   0.2460   0.01202   0.00368  -0.0463   0.4310   0.0175
  -1.000   0.2712   0.01176   0.00340  -0.0458   0.4263   0.0184
  -0.750   0.2969   0.01160   0.00321  -0.0453   0.4224   0.0193
  -0.500   0.3229   0.01142   0.00302  -0.0448   0.4185   0.0200
  -0.250   0.3489   0.01128   0.00284  -0.0444   0.4144   0.0206
   0.000   0.3750   0.01119   0.00270  -0.0440   0.4104   0.0213
   0.250   0.4013   0.01113   0.00259  -0.0436   0.4067   0.0219
   0.500   0.4277   0.01104   0.00248  -0.0432   0.4028   0.0235
   0.750   0.4542   0.01099   0.00241  -0.0429   0.3992   0.0258
   1.000   0.4804   0.01096   0.00238  -0.0425   0.3958   0.0346
   1.250   0.5015   0.01033   0.00241  -0.0415   0.3928   0.2915
   1.500   0.5260   0.00869   0.00271  -0.0407   0.3895   0.9411
   1.750   0.5743   0.00892   0.00287  -0.0448   0.3853   0.9688
   2.000   0.6310   0.00919   0.00303  -0.0508   0.3811   0.9838
   2.250   0.6785   0.00931   0.00307  -0.0551   0.3777   0.9881
   2.500   0.7099   0.00937   0.00311  -0.0560   0.3745   0.9900
   2.750   0.7406   0.00945   0.00315  -0.0567   0.3710   0.9921
   3.000   0.7704   0.00955   0.00321  -0.0572   0.3677   0.9940
   3.250   0.8022   0.00966   0.00326  -0.0583   0.3648   0.9954
   3.500   0.8338   0.00974   0.00332  -0.0593   0.3622   0.9970
   3.750   0.8652   0.00981   0.00340  -0.0602   0.3591   0.9986
   4.000   0.8967   0.00991   0.00348  -0.0612   0.3558   0.9999
   4.250   0.9195   0.01002   0.00358  -0.0603   0.3530   1.0000
   4.500   0.9417   0.01016   0.00369  -0.0593   0.3504   1.0000
   4.750   0.9642   0.01029   0.00382  -0.0583   0.3479   1.0000
   5.000   0.9870   0.01039   0.00395  -0.0574   0.3451   1.0000
   5.250   1.0096   0.01051   0.00408  -0.0565   0.3423   1.0000
   5.500   1.0319   0.01065   0.00423  -0.0556   0.3396   1.0000
   5.750   1.0539   0.01081   0.00439  -0.0546   0.3369   1.0000
   6.000   1.0757   0.01098   0.00455  -0.0535   0.3342   1.0000
   6.250   1.0985   0.01110   0.00472  -0.0527   0.3315   1.0000
   6.500   1.1209   0.01124   0.00490  -0.0517   0.3286   1.0000
   6.750   1.1430   0.01140   0.00507  -0.0508   0.3253   1.0000
   7.000   1.1645   0.01158   0.00526  -0.0497   0.3220   1.0000
   7.250   1.1862   0.01176   0.00546  -0.0487   0.3189   1.0000
   7.500   1.2086   0.01190   0.00566  -0.0478   0.3150   1.0000
   7.750   1.2302   0.01208   0.00587  -0.0468   0.3109   1.0000
   8.000   1.2509   0.01229   0.00608  -0.0457   0.3067   1.0000
   8.250   1.2727   0.01246   0.00631  -0.0448   0.3024   1.0000
   8.500   1.2942   0.01265   0.00655  -0.0438   0.2977   1.0000
   8.750   1.3146   0.01288   0.00679  -0.0426   0.2932   1.0000
   9.000   1.3354   0.01310   0.00706  -0.0416   0.2890   1.0000
   9.250   1.3563   0.01331   0.00733  -0.0405   0.2839   1.0000
   9.500   1.3749   0.01360   0.00762  -0.0391   0.2777   1.0000
   9.750   1.3952   0.01383   0.00792  -0.0381   0.2710   1.0000
  10.000   1.4126   0.01417   0.00826  -0.0365   0.2630   1.0000
  10.250   1.4309   0.01449   0.00861  -0.0352   0.2538   1.0000
  10.500   1.4471   0.01488   0.00901  -0.0335   0.2439   1.0000
  10.750   1.4602   0.01539   0.00949  -0.0314   0.2299   1.0000
  11.000   1.4697   0.01595   0.01003  -0.0287   0.2161   1.0000
  11.250   1.4732   0.01670   0.01071  -0.0250   0.1985   1.0000
  11.500   1.4735   0.01768   0.01160  -0.0213   0.1791   1.0000
  11.750   1.4727   0.01882   0.01267  -0.0177   0.1608   1.0000
  12.000   1.4668   0.02035   0.01413  -0.0141   0.1427   1.0000
  12.250   1.4674   0.02174   0.01552  -0.0118   0.1317   1.0000
  12.500   1.4650   0.02351   0.01729  -0.0097   0.1205   1.0000
  12.750   1.4643   0.02541   0.01922  -0.0082   0.1126   1.0000
  13.000   1.4583   0.02796   0.02178  -0.0071   0.1024   1.0000
  13.250   1.4498   0.03100   0.02483  -0.0063   0.0924   1.0000
  13.500   1.4424   0.03412   0.02798  -0.0059   0.0835   1.0000
  13.750   1.4351   0.03737   0.03128  -0.0057   0.0775   1.0000
  14.000   1.4252   0.04099   0.03494  -0.0056   0.0711   1.0000
  14.250   1.4146   0.04475   0.03876  -0.0057   0.0653   1.0000
  14.500   1.4067   0.04829   0.04237  -0.0059   0.0619   1.0000
  14.750   1.3970   0.05207   0.04622  -0.0062   0.0589   1.0000
  15.000   1.3833   0.05645   0.05065  -0.0067   0.0527   1.0000
  15.250   1.3705   0.06086   0.05510  -0.0073   0.0484   1.0000
  15.500   1.3548   0.06575   0.06001  -0.0082   0.0416   1.0000
  15.750   1.3502   0.06935   0.06369  -0.0089   0.0407   1.0000
  16.000   1.3341   0.07447   0.06882  -0.0100   0.0335   1.0000
  16.250   1.3271   0.07852   0.07293  -0.0109   0.0309   1.0000
  16.500   1.3132   0.08358   0.07800  -0.0122   0.0253   1.0000
  16.750   1.3086   0.08739   0.08188  -0.0132   0.0234   1.0000
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