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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 100,000
Max Cl/Cd: 47.75 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e585-il-100000-n5.txt
Download as CSV file: xf-e585-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 585 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1671   0.08134   0.07648  -0.1020   0.9321   0.0232
  -9.000  -0.1588   0.07722   0.07236  -0.1056   0.9250   0.0227
  -8.750  -0.1524   0.07177   0.06689  -0.1113   0.9180   0.0222
  -8.500  -0.1545   0.06582   0.06089  -0.1174   0.9085   0.0217
  -8.250  -0.1592   0.06031   0.05524  -0.1224   0.9001   0.0211
  -8.000  -0.1717   0.05647   0.05126  -0.1229   0.8886   0.0207
  -7.750  -0.1786   0.05240   0.04696  -0.1232   0.8798   0.0203
  -7.500  -0.1840   0.04771   0.04189  -0.1230   0.8720   0.0196
  -7.000  -0.1827   0.03978   0.03286  -0.1199   0.8575   0.0186
  -6.750  -0.1680   0.03702   0.02969  -0.1194   0.8530   0.0186
  -6.500  -0.1577   0.03490   0.02720  -0.1174   0.8460   0.0186
  -6.250  -0.1375   0.03254   0.02448  -0.1171   0.8418   0.0188
  -6.000  -0.1124   0.03050   0.02209  -0.1174   0.8388   0.0192
  -5.750  -0.0985   0.02929   0.02066  -0.1153   0.8321   0.0195
  -5.500  -0.0744   0.02801   0.01918  -0.1150   0.8280   0.0208
  -5.250  -0.0459   0.02664   0.01744  -0.1152   0.8250   0.0232
  -5.000  -0.0256   0.02563   0.01635  -0.1141   0.8202   0.0248
  -4.750  -0.0049   0.02475   0.01538  -0.1130   0.8152   0.0264
  -4.500   0.0210   0.02372   0.01420  -0.1126   0.8117   0.0285
  -4.250   0.0487   0.02280   0.01324  -0.1128   0.8090   0.0327
  -4.000   0.0645   0.02235   0.01274  -0.1108   0.8031   0.0380
  -3.750   0.0864   0.02173   0.01207  -0.1099   0.7987   0.0469
  -3.500   0.1126   0.02097   0.01136  -0.1098   0.7955   0.0696
  -3.250   0.1399   0.02003   0.01076  -0.1101   0.7930   0.1320
  -3.000   0.1501   0.01948   0.01078  -0.1078   0.7863   0.2472
  -2.750   0.1630   0.01822   0.01087  -0.1054   0.7822   0.5422
  -2.500   0.1808   0.01857   0.01151  -0.1016   0.7792   0.7040
  -2.250   0.1979   0.01904   0.01187  -0.0989   0.7745   0.7480
  -2.000   0.2124   0.01950   0.01222  -0.0957   0.7691   0.7755
  -1.750   0.2340   0.01974   0.01231  -0.0937   0.7657   0.7996
  -1.500   0.2546   0.01993   0.01239  -0.0908   0.7631   0.8216
  -1.250   0.2575   0.02041   0.01285  -0.0855   0.7562   0.8447
  -1.000   0.2691   0.02057   0.01295  -0.0811   0.7519   0.8655
  -0.750   0.2941   0.02051   0.01275  -0.0800   0.7490   0.8785
  -0.500   0.3167   0.02054   0.01266  -0.0792   0.7449   0.8850
  -0.250   0.3304   0.02073   0.01278  -0.0771   0.7385   0.8914
   0.000   0.3595   0.02065   0.01257  -0.0774   0.7352   0.8955
   0.250   0.3929   0.02050   0.01228  -0.0786   0.7327   0.8992
   0.500   0.4027   0.02083   0.01259  -0.0760   0.7254   0.9052
   0.750   0.4290   0.02083   0.01250  -0.0759   0.7213   0.9089
   1.000   0.4617   0.02071   0.01228  -0.0770   0.7185   0.9123
   1.500   0.5003   0.02107   0.01258  -0.0749   0.7072   0.9219
   1.750   0.5323   0.02098   0.01243  -0.0759   0.7041   0.9254
   2.000   0.5687   0.02081   0.01220  -0.0776   0.7017   0.9282
   2.250   0.5745   0.02134   0.01277  -0.0745   0.6929   0.9352
   2.500   0.6072   0.02125   0.01265  -0.0756   0.6893   0.9390
   2.750   0.6451   0.02103   0.01239  -0.0775   0.6868   0.9422
   3.000   0.6544   0.02157   0.01299  -0.0751   0.6778   0.9497
   3.250   0.6895   0.02144   0.01286  -0.0766   0.6740   0.9535
   3.500   0.7299   0.02117   0.01257  -0.0789   0.6713   0.9569
   3.750   0.7434   0.02175   0.01324  -0.0775   0.6619   0.9666
   4.000   0.7822   0.02155   0.01306  -0.0796   0.6582   0.9712
   4.250   0.8068   0.02186   0.01344  -0.0799   0.6507   0.9823
   4.500   0.8372   0.02182   0.01344  -0.0809   0.6449   1.0000
   4.750   0.8770   0.02147   0.01311  -0.0830   0.6413   1.0000
   5.000   0.8812   0.02210   0.01381  -0.0799   0.6311   1.0000
   5.250   0.9217   0.02174   0.01347  -0.0821   0.6268   1.0000
   5.500   0.9291   0.02234   0.01414  -0.0795   0.6167   1.0000
   5.750   0.9701   0.02193   0.01378  -0.0817   0.6118   1.0000
   6.000   0.9784   0.02254   0.01447  -0.0792   0.6011   1.0000
   6.250   1.0071   0.02250   0.01450  -0.0796   0.5937   1.0000
   6.500   1.0293   0.02267   0.01475  -0.0790   0.5844   1.0000
   6.750   1.0464   0.02305   0.01521  -0.0778   0.5741   1.0000
   7.000   1.0785   0.02286   0.01506  -0.0786   0.5657   1.0000
   7.250   1.0962   0.02320   0.01549  -0.0774   0.5541   1.0000
   7.500   1.1125   0.02362   0.01600  -0.0761   0.5419   1.0000
   7.750   1.1320   0.02392   0.01637  -0.0752   0.5294   1.0000
   8.000   1.1523   0.02420   0.01670  -0.0743   0.5162   1.0000
   8.250   1.1713   0.02453   0.01710  -0.0733   0.5019   1.0000
   8.500   1.1888   0.02495   0.01756  -0.0721   0.4867   1.0000
   8.750   1.2052   0.02544   0.01810  -0.0709   0.4706   1.0000
   9.000   1.2209   0.02600   0.01868  -0.0695   0.4536   1.0000
   9.250   1.2361   0.02660   0.01930  -0.0682   0.4360   1.0000
   9.500   1.2506   0.02727   0.01996  -0.0668   0.4177   1.0000
   9.750   1.2600   0.02827   0.02098  -0.0650   0.3985   1.0000
  10.000   1.2692   0.02933   0.02203  -0.0632   0.3791   1.0000
  10.250   1.2778   0.03045   0.02313  -0.0615   0.3596   1.0000
  10.500   1.2851   0.03172   0.02440  -0.0597   0.3406   1.0000
  10.750   1.2908   0.03314   0.02583  -0.0580   0.3214   1.0000
  11.000   1.2958   0.03467   0.02734  -0.0563   0.3027   1.0000
  11.250   1.3000   0.03630   0.02895  -0.0547   0.2845   1.0000
  11.500   1.3034   0.03806   0.03071  -0.0531   0.2666   1.0000
  11.750   1.3063   0.03993   0.03260  -0.0517   0.2491   1.0000
  12.000   1.3085   0.04194   0.03461  -0.0503   0.2319   1.0000
  12.250   1.3100   0.04406   0.03675  -0.0490   0.2154   1.0000
  12.500   1.3110   0.04631   0.03901  -0.0479   0.1997   1.0000
  12.750   1.3116   0.04869   0.04140  -0.0469   0.1845   1.0000
  13.000   1.3118   0.05121   0.04394  -0.0460   0.1699   1.0000
  13.250   1.3114   0.05386   0.04661  -0.0452   0.1560   1.0000
  13.500   1.3109   0.05664   0.04942  -0.0446   0.1427   1.0000
  13.750   1.3099   0.05956   0.05238  -0.0442   0.1301   1.0000
  14.000   1.3086   0.06262   0.05549  -0.0439   0.1182   1.0000
  14.250   1.3068   0.06582   0.05875  -0.0437   0.1074   1.0000
  14.500   1.3038   0.06928   0.06226  -0.0437   0.0974   1.0000
  14.750   1.2994   0.07300   0.06602  -0.0439   0.0886   1.0000
  15.000   1.2973   0.07656   0.06968  -0.0441   0.0798   1.0000
  15.250   1.2934   0.08045   0.07364  -0.0446   0.0725   1.0000
  15.500   1.2874   0.08472   0.07796  -0.0453   0.0661   1.0000
  15.750   1.2841   0.08872   0.08209  -0.0460   0.0599   1.0000
  16.000   1.2767   0.09341   0.08681  -0.0472   0.0552   1.0000
  16.250   1.2732   0.09760   0.09114  -0.0482   0.0502   1.0000
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