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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 100,000
Max Cl/Cd: 45.97 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e639-il-100000-n5.txt
Download as CSV file: xf-e639-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2609   0.10000   0.09560  -0.0311   1.0000   0.0468
  -8.750  -0.2580   0.09716   0.09283  -0.0317   1.0000   0.0478
  -8.500  -0.2569   0.09435   0.09012  -0.0324   1.0000   0.0493
  -8.250  -0.1411   0.07570   0.07137  -0.0507   0.8181   0.0571
  -8.000  -0.1352   0.07239   0.06794  -0.0513   0.7918   0.0583
  -7.750  -0.1331   0.06905   0.06452  -0.0521   0.7706   0.0598
  -7.250  -0.1953   0.07307   0.06843  -0.0592   0.7937   0.0581
  -7.000  -0.1885   0.07010   0.06532  -0.0603   0.7699   0.0594
  -6.750  -0.1824   0.06706   0.06213  -0.0615   0.7500   0.0611
  -6.500  -0.1757   0.06397   0.05889  -0.0627   0.7329   0.0631
  -6.250  -0.1713   0.06245   0.05684  -0.0654   0.7183   0.0676
  -6.000  -0.1629   0.06007   0.05411  -0.0651   0.7047   0.0681
  -5.750  -0.1496   0.05471   0.04883  -0.0652   0.6918   0.0693
  -5.500  -0.1351   0.05161   0.04564  -0.0647   0.6792   0.0703
  -5.250  -0.1160   0.04605   0.03954  -0.0638   0.6698   0.0424
  -5.000  -0.1005   0.04327   0.03657  -0.0631   0.6583   0.0413
  -4.750  -0.0833   0.04069   0.03368  -0.0621   0.6480   0.0412
  -4.500  -0.0653   0.03818   0.03084  -0.0610   0.6382   0.0405
  -4.250  -0.0463   0.03555   0.02785  -0.0598   0.6281   0.0386
  -4.000  -0.0255   0.03242   0.02398  -0.0577   0.6201   0.0356
  -3.750  -0.0028   0.03066   0.02176  -0.0564   0.6106   0.0348
  -3.500   0.0199   0.02892   0.01971  -0.0554   0.6019   0.0345
  -3.250   0.0436   0.02734   0.01777  -0.0544   0.5933   0.0345
  -3.000   0.0683   0.02597   0.01604  -0.0535   0.5847   0.0346
  -2.750   0.0930   0.02470   0.01453  -0.0528   0.5769   0.0359
  -2.500   0.1182   0.02382   0.01353  -0.0522   0.5686   0.0375
  -2.250   0.1446   0.02286   0.01233  -0.0516   0.5616   0.0382
  -2.000   0.1713   0.02195   0.01124  -0.0510   0.5540   0.0387
  -1.750   0.1977   0.02117   0.01030  -0.0504   0.5471   0.0394
  -1.500   0.2236   0.02050   0.00954  -0.0498   0.5401   0.0403
  -1.250   0.2487   0.01993   0.00888  -0.0490   0.5334   0.0416
  -1.000   0.2733   0.01951   0.00834  -0.0481   0.5277   0.0440
  -0.750   0.2972   0.01913   0.00797  -0.0474   0.5212   0.0480
  -0.500   0.3219   0.01886   0.00756  -0.0465   0.5158   0.0517
  -0.250   0.3469   0.01862   0.00721  -0.0458   0.5097   0.0564
   0.000   0.3726   0.01842   0.00693  -0.0452   0.5039   0.0682
   0.500   0.5360   0.01616   0.00682  -0.0659   0.4890   1.0000
   0.750   0.5587   0.01632   0.00677  -0.0650   0.4847   1.0000
   1.000   0.5809   0.01650   0.00685  -0.0640   0.4795   1.0000
   1.250   0.6032   0.01669   0.00693  -0.0631   0.4747   1.0000
   1.500   0.6260   0.01688   0.00697  -0.0622   0.4707   1.0000
   1.750   0.6484   0.01710   0.00709  -0.0612   0.4665   1.0000
   2.000   0.6704   0.01733   0.00728  -0.0603   0.4616   1.0000
   2.250   0.6929   0.01756   0.00740  -0.0593   0.4574   1.0000
   2.500   0.7160   0.01778   0.00750  -0.0585   0.4541   1.0000
   2.750   0.7377   0.01807   0.00779  -0.0575   0.4497   1.0000
   3.000   0.7597   0.01835   0.00805  -0.0565   0.4455   1.0000
   3.250   0.7823   0.01861   0.00824  -0.0556   0.4417   1.0000
   3.500   0.8057   0.01887   0.00839  -0.0549   0.4386   1.0000
   3.750   0.8265   0.01922   0.00880  -0.0538   0.4342   1.0000
   4.000   0.8483   0.01955   0.00916  -0.0528   0.4303   1.0000
   4.250   0.8708   0.01985   0.00942  -0.0520   0.4269   1.0000
   4.500   0.8944   0.02013   0.00962  -0.0513   0.4239   1.0000
   4.750   0.9147   0.02054   0.01012  -0.0501   0.4197   1.0000
   5.000   0.9356   0.02092   0.01057  -0.0491   0.4158   1.0000
   5.250   0.9578   0.02127   0.01092  -0.0482   0.4125   1.0000
   5.500   0.9812   0.02158   0.01119  -0.0476   0.4096   1.0000
   5.750   1.0016   0.02202   0.01172  -0.0465   0.4059   1.0000
   6.000   1.0211   0.02249   0.01230  -0.0453   0.4018   1.0000
   6.250   1.0423   0.02290   0.01275  -0.0444   0.3984   1.0000
   6.500   1.0652   0.02324   0.01309  -0.0437   0.3954   1.0000
   6.750   1.0871   0.02365   0.01356  -0.0428   0.3923   1.0000
   7.000   1.1041   0.02425   0.01433  -0.0414   0.3879   1.0000
   7.250   1.1241   0.02473   0.01490  -0.0403   0.3843   1.0000
   7.500   1.1465   0.02510   0.01530  -0.0396   0.3811   1.0000
   7.750   1.1700   0.02545   0.01569  -0.0391   0.3782   1.0000
   8.000   1.1836   0.02622   0.01668  -0.0373   0.3736   1.0000
   8.250   1.2020   0.02675   0.01734  -0.0361   0.3695   1.0000
   8.500   1.2243   0.02709   0.01772  -0.0354   0.3661   1.0000
   8.750   1.2454   0.02752   0.01824  -0.0345   0.3627   1.0000
   9.000   1.2564   0.02837   0.01932  -0.0325   0.3576   1.0000
   9.250   1.2748   0.02882   0.01987  -0.0313   0.3533   1.0000
   9.500   1.2997   0.02898   0.02005  -0.0310   0.3498   1.0000
   9.750   1.3070   0.02993   0.02127  -0.0285   0.3444   1.0000
  10.000   1.3207   0.03052   0.02200  -0.0268   0.3395   1.0000
  10.250   1.3448   0.03060   0.02211  -0.0263   0.3354   1.0000
  10.500   1.3477   0.03165   0.02339  -0.0235   0.3299   1.0000
  10.750   1.3571   0.03232   0.02421  -0.0213   0.3246   1.0000
  11.000   1.3825   0.03222   0.02413  -0.0209   0.3201   1.0000
  11.250   1.3684   0.03382   0.02599  -0.0161   0.3145   1.0000
  11.500   1.3736   0.03454   0.02683  -0.0137   0.3092   1.0000
  11.750   1.3852   0.03503   0.02740  -0.0120   0.3043   1.0000
  12.000   1.3655   0.03743   0.03002  -0.0085   0.2984   1.0000
  12.250   1.3790   0.03784   0.03049  -0.0073   0.2927   1.0000
  12.500   1.3545   0.04132   0.03416  -0.0052   0.2867   1.0000
  12.750   1.3495   0.04352   0.03647  -0.0043   0.2801   1.0000
  13.000   1.3286   0.04762   0.04071  -0.0039   0.2737   1.0000
  13.250   1.3086   0.05205   0.04525  -0.0040   0.2664   1.0000
  13.500   1.2591   0.06063   0.05392  -0.0057   0.2579   1.0000
  13.750   1.2760   0.06088   0.05426  -0.0052   0.2512   1.0000
  14.000   1.2156   0.07183   0.06525  -0.0081   0.2405   1.0000
  14.250   1.2559   0.06871   0.06223  -0.0064   0.2355   1.0000
  14.500   1.2118   0.07786   0.07144  -0.0091   0.2249   1.0000
  14.750   1.1883   0.08438   0.07804  -0.0110   0.2153   1.0000
  15.000   1.2188   0.08250   0.07623  -0.0098   0.2097   1.0000
  15.250   1.1909   0.08993   0.08373  -0.0121   0.1998   1.0000
  15.500   1.2047   0.09070   0.08456  -0.0120   0.1928   1.0000
  15.750   1.2008   0.09442   0.08834  -0.0130   0.1843   1.0000
  16.000   1.1945   0.09861   0.09261  -0.0143   0.1762   1.0000
  16.250   1.2170   0.09785   0.09183  -0.0136   0.1686   1.0000
  16.500   1.1973   0.10448   0.09858  -0.0160   0.1602   1.0000
  16.750   1.2037   0.10654   0.10065  -0.0165   0.1525   1.0000
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