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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 100,000
Max Cl/Cd: 50.35 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e585-il-100000.txt
Download as CSV file: xf-e585-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2777   0.10690   0.10268  -0.0637   0.9667   0.0933
  -8.500  -0.2982   0.10326   0.09911  -0.0743   0.9593   0.0960
  -8.250  -0.3249   0.10073   0.09662  -0.0775   0.9494   0.0962
  -8.000  -0.2667   0.09597   0.09182  -0.0716   0.9508   0.1017
  -7.750  -0.2606   0.09238   0.08823  -0.0754   0.9462   0.1064
  -7.500  -0.2861   0.08998   0.08589  -0.0768   0.9366   0.1087
  -7.250  -0.3206   0.08692   0.08278  -0.0818   0.9268   0.1103
  -7.000  -0.3437   0.08351   0.07921  -0.0838   0.9183   0.1118
  -6.750  -0.3024   0.07986   0.07576  -0.0812   0.9177   0.1167
  -6.500  -0.3102   0.07759   0.07346  -0.0804   0.9110   0.1206
  -6.250  -0.3344   0.07427   0.06981  -0.0833   0.9028   0.1274
  -6.000  -0.3041   0.07066   0.06636  -0.0834   0.9008   0.1329
  -5.750  -0.3191   0.06942   0.06506  -0.0798   0.8932   0.1371
  -5.500  -0.3133   0.06601   0.06152  -0.0807   0.8885   0.1462
  -4.500  -0.2327   0.04630   0.03949  -0.0850   0.8719   0.0646
  -4.250  -0.1903   0.04198   0.03429  -0.0870   0.8698   0.0537
  -4.000  -0.1861   0.04091   0.03295  -0.0836   0.8635   0.0532
  -3.750  -0.1580   0.03931   0.03092  -0.0838   0.8596   0.0543
  -3.500  -0.1206   0.03779   0.02892  -0.0849   0.8565   0.0560
  -3.250  -0.0783   0.03558   0.02651  -0.0869   0.8543   0.0580
  -3.000  -0.0778   0.03537   0.02631  -0.0830   0.8474   0.0594
  -2.750  -0.0486   0.03475   0.02555  -0.0831   0.8433   0.0683
  -2.500  -0.0121   0.03331   0.02431  -0.0845   0.8404   0.0859
  -2.250   0.0020   0.03283   0.02403  -0.0827   0.8348   0.1166
  -2.000   0.0106   0.02998   0.02403  -0.0798   0.8305   0.6065
  -1.750   0.0100   0.03107   0.02534  -0.0707   0.8258   0.8044
  -1.500   0.0033   0.03181   0.02603  -0.0630   0.8199   0.8460
  -1.250  -0.0035   0.03221   0.02638  -0.0552   0.8137   0.8799
  -1.000   0.0047   0.03229   0.02634  -0.0491   0.8097   0.9210
  -0.750   0.2636   0.03342   0.02660  -0.0889   0.8122   1.0000
  -0.500   0.2996   0.03336   0.02635  -0.0908   0.8090   1.0000
  -0.250   0.2645   0.03429   0.02732  -0.0819   0.7983   1.0000
   0.000   0.2952   0.03432   0.02719  -0.0829   0.7945   1.0000
   0.250   0.2669   0.03512   0.02799  -0.0751   0.7847   1.0000
   0.500   0.2918   0.03519   0.02794  -0.0751   0.7799   1.0000
   0.750   0.2725   0.03582   0.02855  -0.0687   0.7709   1.0000
   1.000   0.2911   0.03595   0.02858  -0.0677   0.7653   1.0000
   1.250   0.3331   0.03592   0.02841  -0.0700   0.7623   1.0000
   1.500   0.3037   0.03670   0.02920  -0.0625   0.7507   1.0000
   1.750   0.3472   0.03669   0.02906  -0.0650   0.7475   1.0000
   2.000   0.3411   0.03771   0.03005  -0.0617   0.7365   1.0000
   2.250   0.3843   0.03772   0.02997  -0.0641   0.7329   1.0000
   2.500   0.3890   0.03880   0.03102  -0.0624   0.7222   1.0000
   2.750   0.4310   0.03880   0.03095  -0.0647   0.7182   1.0000
   3.000   0.4406   0.03990   0.03203  -0.0637   0.7079   1.0000
   3.250   0.4812   0.03990   0.03198  -0.0657   0.7035   1.0000
   3.500   0.4941   0.04098   0.03305  -0.0651   0.6935   1.0000
   3.750   0.5336   0.04095   0.03299  -0.0668   0.6887   1.0000
   4.000   0.5810   0.04055   0.03257  -0.0693   0.6861   1.0000
   4.250   0.5879   0.04185   0.03389  -0.0680   0.6738   1.0000
   4.500   0.6330   0.04141   0.03345  -0.0701   0.6706   1.0000
   4.750   0.6434   0.04258   0.03463  -0.0691   0.6588   1.0000
   5.000   0.6873   0.04205   0.03415  -0.0709   0.6553   1.0000
   5.250   0.6998   0.04312   0.03523  -0.0701   0.6438   1.0000
   5.500   0.7496   0.04205   0.03421  -0.0721   0.6416   1.0000
   6.000   0.8013   0.04249   0.03476  -0.0722   0.6252   1.0000
   6.250   0.8170   0.04330   0.03562  -0.0715   0.6141   1.0000
   6.500   0.8593   0.04227   0.03467  -0.0725   0.6099   1.0000
   6.750   0.8787   0.04273   0.03521  -0.0719   0.5994   1.0000
   7.000   0.8943   0.04351   0.03606  -0.0710   0.5881   1.0000
   7.250   0.9436   0.04153   0.03420  -0.0721   0.5852   1.0000
   7.500   1.0008   0.03873   0.03155  -0.0737   0.5842   1.0000
   7.750   1.0668   0.03545   0.02844  -0.0763   0.5832   1.0000
   8.000   1.1499   0.03157   0.02475  -0.0813   0.5819   1.0000
   8.250   1.1635   0.03173   0.02502  -0.0792   0.5689   1.0000
   8.500   1.1870   0.03136   0.02476  -0.0782   0.5566   1.0000
   8.750   1.2287   0.02999   0.02352  -0.0792   0.5451   1.0000
   9.000   1.2723   0.02862   0.02227  -0.0804   0.5317   1.0000
   9.250   1.3020   0.02800   0.02173  -0.0800   0.5155   1.0000
   9.500   1.3277   0.02760   0.02138  -0.0792   0.4975   1.0000
   9.750   1.3604   0.02702   0.02078  -0.0793   0.4774   1.0000
  10.000   1.3632   0.02774   0.02156  -0.0758   0.4570   1.0000
  10.250   1.3776   0.02809   0.02187  -0.0738   0.4350   1.0000
  10.500   1.3845   0.02888   0.02264  -0.0711   0.4129   1.0000
  10.750   1.3903   0.02979   0.02350  -0.0684   0.3904   1.0000
  11.000   1.3934   0.03095   0.02461  -0.0656   0.3682   1.0000
  11.250   1.3947   0.03227   0.02588  -0.0628   0.3462   1.0000
  11.500   1.3961   0.03372   0.02728  -0.0602   0.3247   1.0000
  11.750   1.3940   0.03546   0.02900  -0.0575   0.3037   1.0000
  12.000   1.3948   0.03714   0.03055  -0.0552   0.2833   1.0000
  12.250   1.3904   0.03924   0.03267  -0.0529   0.2637   1.0000
  12.500   1.3870   0.04140   0.03480  -0.0507   0.2447   1.0000
  12.750   1.3841   0.04362   0.03695  -0.0488   0.2264   1.0000
  13.000   1.3803   0.04605   0.03931  -0.0471   0.2086   1.0000
  13.250   1.3751   0.04872   0.04201  -0.0455   0.1915   1.0000
  13.500   1.3700   0.05152   0.04480  -0.0441   0.1751   1.0000
  13.750   1.3646   0.05448   0.04775  -0.0429   0.1593   1.0000
  14.000   1.3595   0.05756   0.05080  -0.0419   0.1446   1.0000
  14.250   1.3547   0.06076   0.05397  -0.0410   0.1307   1.0000
  14.500   1.3500   0.06408   0.05728  -0.0404   0.1177   1.0000
  14.750   1.3464   0.06745   0.06065  -0.0398   0.1058   1.0000
  15.000   1.3432   0.07086   0.06408  -0.0394   0.0950   1.0000
  15.250   1.3418   0.07415   0.06733  -0.0391   0.0855   1.0000
  15.500   1.3429   0.07718   0.07023  -0.0388   0.0763   1.0000
  15.750   1.3373   0.08124   0.07457  -0.0390   0.0700   1.0000
  16.000   1.3392   0.08439   0.07770  -0.0388   0.0631   1.0000
  16.250   1.3366   0.08816   0.08163  -0.0391   0.0579   1.0000
  16.500   1.3395   0.09140   0.08491  -0.0391   0.0526   1.0000
  16.750   1.3349   0.09563   0.08939  -0.0398   0.0490   1.0000
  17.000   1.3420   0.09842   0.09209  -0.0397   0.0444   1.0000
  17.250   1.3317   0.10354   0.09757  -0.0410   0.0425   1.0000
  17.500   1.3240   0.10840   0.10266  -0.0425   0.0403   1.0000
  17.750   1.3272   0.11161   0.10586  -0.0432   0.0376   1.0000
  18.000   1.3210   0.11667   0.11111  -0.0446   0.0360   1.0000
  18.250   1.3041   0.12320   0.11796  -0.0476   0.0355   1.0000
  18.500   1.2869   0.13012   0.12517  -0.0511   0.0350   1.0000
  18.750   1.2692   0.13745   0.13277  -0.0552   0.0348   1.0000
  19.000   1.2500   0.14541   0.14098  -0.0599   0.0349   1.0000
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