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EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il)
Reynolds number: 200,000
Max Cl/Cd: 34.68 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ea61012-il-200000.txt
Download as CSV file: xf-ea61012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 6(-1)-012 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6744   0.12052   0.11658   0.0005   1.0000   0.0930
 -12.250  -0.6527   0.11966   0.11569   0.0028   1.0000   0.0946
 -12.000  -0.8951   0.06951   0.06516  -0.0324   1.0000   0.0694
 -11.750  -0.9118   0.06485   0.06033  -0.0326   1.0000   0.0670
 -11.500  -0.9332   0.06059   0.05592  -0.0318   1.0000   0.0666
 -11.250  -0.9565   0.05703   0.05217  -0.0292   1.0000   0.0664
 -11.000  -0.9722   0.05326   0.04815  -0.0269   1.0000   0.0663
 -10.750  -0.9819   0.04976   0.04433  -0.0246   1.0000   0.0666
 -10.500  -0.9859   0.04665   0.04086  -0.0223   1.0000   0.0671
 -10.250  -0.9842   0.04403   0.03786  -0.0202   1.0000   0.0676
  -9.750  -0.9684   0.03753   0.03076  -0.0174   1.0000   0.0693
  -9.500  -0.9499   0.03549   0.02866  -0.0168   1.0000   0.0707
  -9.250  -0.9299   0.03383   0.02693  -0.0162   1.0000   0.0718
  -9.000  -0.9108   0.03213   0.02507  -0.0154   1.0000   0.0729
  -8.750  -0.8908   0.03066   0.02342  -0.0146   1.0000   0.0744
  -8.500  -0.8704   0.02920   0.02177  -0.0138   1.0000   0.0758
  -8.250  -0.8489   0.02776   0.02013  -0.0130   1.0000   0.0768
  -8.000  -0.8266   0.02650   0.01868  -0.0123   1.0000   0.0779
  -7.750  -0.8042   0.02565   0.01763  -0.0115   1.0000   0.0790
  -7.500  -0.7805   0.02374   0.01566  -0.0112   1.0000   0.0806
  -7.250  -0.7567   0.02249   0.01444  -0.0108   1.0000   0.0822
  -7.000  -0.7348   0.02158   0.01353  -0.0100   1.0000   0.0836
  -6.750  -0.7186   0.02087   0.01282  -0.0083   1.0000   0.0850
  -6.500  -0.7032   0.02029   0.01222  -0.0067   0.9977   0.0867
  -6.250  -0.6649   0.01949   0.01136  -0.0092   0.9891   0.0894
  -6.000  -0.6256   0.01879   0.01057  -0.0117   0.9823   0.0915
  -5.750  -0.5908   0.01755   0.00943  -0.0135   0.9746   0.0944
  -5.250  -0.5194   0.01621   0.00813  -0.0174   0.9594   0.1025
  -5.000  -0.4842   0.01547   0.00742  -0.0192   0.9527   0.1072
  -4.750  -0.4544   0.01486   0.00687  -0.0200   0.9432   0.1135
  -4.500  -0.4241   0.01430   0.00633  -0.0207   0.9352   0.1225
  -4.250  -0.3988   0.01373   0.00588  -0.0205   0.9260   0.1398
  -4.000  -0.3798   0.01262   0.00532  -0.0195   0.9176   0.2288
  -3.750  -0.3683   0.01126   0.00491  -0.0173   0.9085   0.4206
  -3.500  -0.3512   0.01077   0.00509  -0.0150   0.9015   0.5631
  -3.250  -0.3273   0.01083   0.00527  -0.0138   0.8944   0.6194
  -3.000  -0.3019   0.01100   0.00546  -0.0128   0.8886   0.6522
  -2.750  -0.2765   0.01120   0.00567  -0.0119   0.8822   0.6758
  -2.500  -0.2505   0.01142   0.00588  -0.0110   0.8764   0.6936
  -2.250  -0.2243   0.01167   0.00609  -0.0102   0.8718   0.7094
  -2.000  -0.1989   0.01199   0.00642  -0.0092   0.8658   0.7263
  -1.750  -0.1742   0.01229   0.00672  -0.0079   0.8591   0.7422
  -1.500  -0.1497   0.01256   0.00696  -0.0065   0.8530   0.7566
  -1.250  -0.1252   0.01283   0.00729  -0.0051   0.8461   0.7703
  -1.000  -0.1012   0.01309   0.00757  -0.0033   0.8405   0.7846
  -0.750  -0.0770   0.01325   0.00775  -0.0019   0.8345   0.7960
  -0.500  -0.0520   0.01329   0.00776  -0.0013   0.8276   0.8050
  -0.250  -0.0260   0.01327   0.00773  -0.0004   0.8222   0.8097
   0.000   0.0000   0.01327   0.00776   0.0000   0.8154   0.8154
   0.250   0.0259   0.01327   0.00773   0.0004   0.8097   0.8222
   0.500   0.0519   0.01329   0.00776   0.0013   0.8050   0.8277
   0.750   0.0769   0.01325   0.00775   0.0020   0.7959   0.8345
   1.000   0.1011   0.01309   0.00757   0.0034   0.7845   0.8405
   1.250   0.1251   0.01284   0.00729   0.0051   0.7705   0.8461
   1.500   0.1497   0.01256   0.00696   0.0065   0.7566   0.8530
   1.750   0.1742   0.01229   0.00672   0.0079   0.7422   0.8591
   2.000   0.1988   0.01198   0.00642   0.0092   0.7262   0.8658
   2.250   0.2242   0.01167   0.00609   0.0102   0.7094   0.8718
   2.500   0.2504   0.01142   0.00588   0.0111   0.6936   0.8764
   2.750   0.2765   0.01120   0.00567   0.0119   0.6758   0.8822
   3.000   0.3019   0.01100   0.00546   0.0128   0.6523   0.8886
   3.250   0.3273   0.01083   0.00527   0.0138   0.6192   0.8944
   3.500   0.3511   0.01077   0.00509   0.0150   0.5628   0.9015
   3.750   0.3682   0.01126   0.00491   0.0173   0.4207   0.9085
   4.000   0.3799   0.01260   0.00531   0.0195   0.2302   0.9176
   4.250   0.3988   0.01373   0.00588   0.0205   0.1399   0.9260
   4.500   0.4241   0.01430   0.00633   0.0207   0.1224   0.9353
   4.750   0.4544   0.01486   0.00687   0.0200   0.1135   0.9432
   5.000   0.4842   0.01547   0.00742   0.0192   0.1072   0.9527
   5.250   0.5195   0.01620   0.00813   0.0174   0.1025   0.9594
   5.500   0.5534   0.01678   0.00871   0.0159   0.0981   0.9683
   5.750   0.5909   0.01754   0.00943   0.0135   0.0944   0.9747
   6.000   0.6258   0.01879   0.01057   0.0116   0.0915   0.9824
   6.250   0.6650   0.01949   0.01136   0.0091   0.0894   0.9891
   6.500   0.7033   0.02028   0.01221   0.0067   0.0867   0.9978
   6.750   0.7185   0.02086   0.01282   0.0084   0.0850   1.0000
   7.000   0.7348   0.02157   0.01353   0.0100   0.0836   1.0000
   7.250   0.7567   0.02248   0.01443   0.0108   0.0822   1.0000
   7.500   0.7805   0.02375   0.01566   0.0112   0.0806   1.0000
   7.750   0.8041   0.02563   0.01761   0.0115   0.0790   1.0000
   8.000   0.8266   0.02649   0.01867   0.0123   0.0778   1.0000
   8.250   0.8489   0.02776   0.02013   0.0130   0.0768   1.0000
   8.500   0.8704   0.02919   0.02176   0.0138   0.0757   1.0000
   8.750   0.8909   0.03064   0.02341   0.0146   0.0743   1.0000
   9.000   0.9109   0.03211   0.02504   0.0154   0.0729   1.0000
   9.250   0.9300   0.03384   0.02694   0.0162   0.0718   1.0000
   9.500   0.9499   0.03549   0.02866   0.0168   0.0707   1.0000
   9.750   0.9685   0.03754   0.03076   0.0174   0.0693   1.0000
  10.250   0.9841   0.04402   0.03785   0.0202   0.0676   1.0000
  10.500   0.9860   0.04667   0.04088   0.0223   0.0671   1.0000
  10.750   0.9824   0.04984   0.04441   0.0245   0.0667   1.0000
  11.000   0.9723   0.05330   0.04819   0.0268   0.0663   1.0000
  11.250   0.9560   0.05696   0.05211   0.0292   0.0663   1.0000
  11.500   0.9340   0.06066   0.05599   0.0317   0.0666   1.0000
  11.750   0.9130   0.06496   0.06043   0.0325   0.0671   1.0000
  12.000   0.8966   0.07018   0.06574   0.0321   0.0677   1.0000
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