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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 200,000
Max Cl/Cd: 69.25 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e639-il-200000-n5.txt
Download as CSV file: xf-e639-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2831   0.11465   0.11122  -0.0260   1.0000   0.0215
 -10.250  -0.2875   0.11133   0.10795  -0.0296   1.0000   0.0219
 -10.000  -0.2856   0.10805   0.10472  -0.0314   1.0000   0.0219
  -9.750  -0.2765   0.10436   0.10108  -0.0298   1.0000   0.0224
  -9.500  -0.2703   0.10144   0.09819  -0.0298   1.0000   0.0227
  -9.250  -0.2420   0.09679   0.09350  -0.0361   0.9138   0.0237
  -9.000  -0.1996   0.09032   0.08672  -0.0486   0.8409   0.0252
  -8.750  -0.1874   0.08647   0.08267  -0.0528   0.7942   0.0261
  -8.500  -0.1868   0.08303   0.07912  -0.0558   0.7647   0.0271
  -8.250  -0.1931   0.07938   0.07541  -0.0598   0.7420   0.0275
  -8.000  -0.1971   0.07604   0.07200  -0.0622   0.7226   0.0276
  -7.750  -0.2043   0.07247   0.06832  -0.0645   0.7071   0.0278
  -7.500  -0.2036   0.06894   0.06464  -0.0660   0.6929   0.0278
  -7.250  -0.2014   0.06503   0.06065  -0.0663   0.6800   0.0281
  -7.000  -0.1949   0.06208   0.05762  -0.0658   0.6668   0.0284
  -6.750  -0.1865   0.05971   0.05519  -0.0651   0.6537   0.0289
  -6.500  -0.1773   0.05727   0.05265  -0.0649   0.6416   0.0298
  -6.250  -0.1676   0.05444   0.04968  -0.0650   0.6310   0.0304
  -6.000  -0.1548   0.05159   0.04624  -0.0654   0.6226   0.0349
  -5.500  -0.1317   0.04508   0.03964  -0.0645   0.6035   0.0363
  -5.250  -0.1164   0.04282   0.03723  -0.0638   0.5939   0.0371
  -5.000  -0.0999   0.04054   0.03476  -0.0630   0.5849   0.0381
  -4.750  -0.0826   0.03814   0.03211  -0.0620   0.5765   0.0388
  -4.250  -0.0488   0.02774   0.02034  -0.0565   0.5636   0.0224
  -4.000  -0.0272   0.02667   0.01916  -0.0558   0.5553   0.0231
  -3.750  -0.0048   0.02564   0.01793  -0.0551   0.5473   0.0244
  -3.500   0.0181   0.02378   0.01571  -0.0538   0.5403   0.0242
  -3.250   0.0420   0.02195   0.01348  -0.0526   0.5330   0.0237
  -3.000   0.0670   0.02054   0.01173  -0.0516   0.5260   0.0236
  -2.750   0.0927   0.01943   0.01034  -0.0508   0.5187   0.0236
  -2.500   0.1186   0.01853   0.00923  -0.0502   0.5122   0.0239
  -2.250   0.1448   0.01775   0.00830  -0.0496   0.5055   0.0243
  -2.000   0.1706   0.01713   0.00753  -0.0490   0.4997   0.0250
  -1.750   0.1966   0.01664   0.00696  -0.0485   0.4934   0.0265
  -1.500   0.2223   0.01621   0.00641  -0.0479   0.4874   0.0274
  -1.250   0.2473   0.01577   0.00589  -0.0472   0.4821   0.0278
  -1.000   0.2717   0.01528   0.00538  -0.0464   0.4762   0.0284
  -0.750   0.2961   0.01495   0.00500  -0.0457   0.4714   0.0294
  -0.500   0.3210   0.01473   0.00472  -0.0450   0.4668   0.0307
  -0.250   0.3464   0.01455   0.00449  -0.0444   0.4616   0.0324
   0.000   0.3717   0.01443   0.00430  -0.0439   0.4568   0.0359
   0.250   0.3971   0.01434   0.00415  -0.0433   0.4525   0.0418
   0.500   0.4224   0.01418   0.00405  -0.0427   0.4477   0.0619
   1.000   0.5962   0.01229   0.00441  -0.0665   0.4352   1.0000
   1.250   0.6190   0.01237   0.00441  -0.0656   0.4308   1.0000
   1.500   0.6416   0.01248   0.00442  -0.0647   0.4270   1.0000
   1.750   0.6642   0.01261   0.00444  -0.0638   0.4239   1.0000
   2.000   0.6871   0.01273   0.00452  -0.0629   0.4202   1.0000
   2.250   0.7098   0.01284   0.00460  -0.0620   0.4163   1.0000
   2.500   0.7324   0.01298   0.00468  -0.0610   0.4126   1.0000
   2.750   0.7549   0.01314   0.00475  -0.0601   0.4095   1.0000
   3.000   0.7777   0.01330   0.00488  -0.0592   0.4064   1.0000
   3.250   0.8004   0.01345   0.00503  -0.0583   0.4030   1.0000
   3.500   0.8230   0.01361   0.00517  -0.0574   0.3995   1.0000
   3.750   0.8455   0.01378   0.00530  -0.0564   0.3963   1.0000
   4.000   0.8680   0.01399   0.00544  -0.0555   0.3935   1.0000
   4.250   0.8906   0.01416   0.00566  -0.0546   0.3902   1.0000
   4.500   0.9131   0.01435   0.00587  -0.0537   0.3869   1.0000
   4.750   0.9356   0.01454   0.00607  -0.0528   0.3837   1.0000
   5.000   0.9580   0.01475   0.00626  -0.0519   0.3808   1.0000
   5.250   0.9806   0.01498   0.00645  -0.0510   0.3780   1.0000
   5.500   1.0028   0.01520   0.00674  -0.0501   0.3748   1.0000
   5.750   1.0250   0.01542   0.00702  -0.0492   0.3716   1.0000
   6.000   1.0472   0.01564   0.00726  -0.0483   0.3684   1.0000
   6.250   1.0696   0.01587   0.00748  -0.0474   0.3656   1.0000
   6.500   1.0919   0.01614   0.00776  -0.0466   0.3629   1.0000
   6.750   1.1136   0.01639   0.00812  -0.0456   0.3596   1.0000
   7.000   1.1353   0.01664   0.00844  -0.0447   0.3561   1.0000
   7.250   1.1570   0.01688   0.00872  -0.0438   0.3529   1.0000
   7.500   1.1791   0.01715   0.00900  -0.0429   0.3501   1.0000
   7.750   1.2002   0.01744   0.00937  -0.0419   0.3467   1.0000
   8.000   1.2209   0.01771   0.00975  -0.0409   0.3428   1.0000
   8.250   1.2417   0.01797   0.01008  -0.0398   0.3390   1.0000
   8.500   1.2630   0.01824   0.01037  -0.0389   0.3355   1.0000
   8.750   1.2828   0.01854   0.01079  -0.0377   0.3313   1.0000
   9.000   1.3023   0.01883   0.01119  -0.0365   0.3265   1.0000
   9.250   1.3220   0.01909   0.01150  -0.0354   0.3222   1.0000
   9.500   1.3410   0.01941   0.01191  -0.0342   0.3176   1.0000
   9.750   1.3591   0.01973   0.01238  -0.0328   0.3124   1.0000
  10.000   1.3772   0.02004   0.01274  -0.0315   0.3078   1.0000
  10.250   1.3946   0.02040   0.01321  -0.0301   0.3029   1.0000
  10.500   1.4105   0.02077   0.01372  -0.0285   0.2970   1.0000
  10.750   1.4253   0.02112   0.01409  -0.0267   0.2915   1.0000
  11.000   1.4385   0.02156   0.01471  -0.0247   0.2846   1.0000
  11.250   1.4481   0.02199   0.01518  -0.0221   0.2784   1.0000
  11.500   1.4569   0.02252   0.01584  -0.0196   0.2712   1.0000
  11.750   1.4644   0.02312   0.01651  -0.0171   0.2646   1.0000
  12.000   1.4723   0.02383   0.01735  -0.0148   0.2572   1.0000
  12.250   1.4761   0.02473   0.01829  -0.0124   0.2493   1.0000
  12.500   1.4801   0.02579   0.01947  -0.0103   0.2400   1.0000
  12.750   1.4803   0.02718   0.02092  -0.0083   0.2297   1.0000
  13.000   1.4767   0.02901   0.02278  -0.0065   0.2178   1.0000
  13.250   1.4701   0.03132   0.02512  -0.0051   0.2053   1.0000
  13.500   1.4613   0.03410   0.02791  -0.0042   0.1933   1.0000
  13.750   1.4493   0.03742   0.03124  -0.0036   0.1811   1.0000
  14.000   1.4354   0.04115   0.03498  -0.0034   0.1696   1.0000
  14.250   1.4218   0.04503   0.03892  -0.0034   0.1592   1.0000
  14.500   1.4079   0.04910   0.04303  -0.0036   0.1508   1.0000
  14.750   1.3937   0.05331   0.04728  -0.0040   0.1437   1.0000
  15.000   1.3773   0.05797   0.05197  -0.0047   0.1344   1.0000
  15.250   1.3624   0.06261   0.05665  -0.0055   0.1271   1.0000
  15.500   1.3482   0.06735   0.06142  -0.0065   0.1194   1.0000
  15.750   1.3382   0.07163   0.06576  -0.0075   0.1140   1.0000
  16.000   1.3251   0.07645   0.07062  -0.0087   0.1067   1.0000
  16.250   1.3135   0.08119   0.07539  -0.0100   0.0994   1.0000
  16.500   1.3018   0.08602   0.08025  -0.0114   0.0934   1.0000
  16.750   1.2945   0.09031   0.08460  -0.0127   0.0878   1.0000
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