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EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il)
Reynolds number: 200,000
Max Cl/Cd: 37.27 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ea61012-il-200000-n5.txt
Download as CSV file: xf-ea61012-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.9907   0.07311   0.06853  -0.0276   1.0000   0.0394
 -14.250  -1.0288   0.06467   0.05980  -0.0324   1.0000   0.0395
 -14.000  -1.0551   0.05880   0.05368  -0.0348   1.0000   0.0399
 -13.750  -1.0759   0.05411   0.04873  -0.0358   1.0000   0.0403
 -13.500  -1.0919   0.05035   0.04470  -0.0358   1.0000   0.0408
 -13.250  -1.1047   0.04721   0.04130  -0.0352   1.0000   0.0413
 -13.000  -1.1141   0.04471   0.03852  -0.0339   1.0000   0.0418
 -12.750  -1.1189   0.04252   0.03612  -0.0323   1.0000   0.0423
 -12.500  -1.1138   0.04080   0.03434  -0.0310   1.0000   0.0430
 -12.250  -1.1066   0.03961   0.03312  -0.0294   1.0000   0.0436
 -12.000  -1.0991   0.03857   0.03202  -0.0276   1.0000   0.0442
 -11.750  -1.0910   0.03747   0.03080  -0.0259   1.0000   0.0450
 -11.500  -1.0806   0.03622   0.02942  -0.0244   1.0000   0.0457
 -11.250  -1.0687   0.03493   0.02797  -0.0230   1.0000   0.0466
 -11.000  -1.0553   0.03356   0.02642  -0.0218   1.0000   0.0475
 -10.750  -1.0403   0.03229   0.02496  -0.0206   1.0000   0.0484
 -10.500  -1.0242   0.03111   0.02358  -0.0195   1.0000   0.0494
 -10.250  -1.0069   0.03004   0.02229  -0.0184   1.0000   0.0503
 -10.000  -0.9881   0.02902   0.02107  -0.0175   1.0000   0.0509
  -9.750  -0.9669   0.02760   0.01960  -0.0170   1.0000   0.0517
  -9.500  -0.9454   0.02655   0.01853  -0.0165   1.0000   0.0525
  -9.250  -0.9238   0.02566   0.01762  -0.0159   1.0000   0.0533
  -9.000  -0.9020   0.02485   0.01677  -0.0153   1.0000   0.0542
  -8.750  -0.8800   0.02410   0.01595  -0.0147   1.0000   0.0553
  -8.500  -0.8578   0.02336   0.01516  -0.0141   1.0000   0.0566
  -8.250  -0.8352   0.02262   0.01434  -0.0135   1.0000   0.0576
  -8.000  -0.8124   0.02190   0.01356  -0.0129   1.0000   0.0585
  -7.750  -0.7896   0.02123   0.01283  -0.0123   1.0000   0.0593
  -7.500  -0.7639   0.02050   0.01206  -0.0123   0.9812   0.0601
  -7.000  -0.6960   0.01888   0.01043  -0.0159   0.9207   0.0628
  -6.750  -0.6670   0.01831   0.00981  -0.0164   0.9033   0.0642
  -6.500  -0.6408   0.01785   0.00928  -0.0163   0.8898   0.0660
  -6.250  -0.6158   0.01744   0.00878  -0.0160   0.8789   0.0678
  -6.000  -0.5914   0.01704   0.00832  -0.0154   0.8698   0.0693
  -5.500  -0.5451   0.01607   0.00732  -0.0141   0.8552   0.0728
  -5.250  -0.5210   0.01572   0.00692  -0.0135   0.8489   0.0749
  -5.000  -0.4966   0.01540   0.00655  -0.0130   0.8430   0.0773
  -4.750  -0.4722   0.01507   0.00619  -0.0124   0.8369   0.0801
  -4.500  -0.4482   0.01473   0.00584  -0.0117   0.8316   0.0841
  -4.250  -0.4232   0.01444   0.00554  -0.0113   0.8263   0.0898
  -4.000  -0.3988   0.01408   0.00525  -0.0107   0.8212   0.0999
  -3.750  -0.3748   0.01369   0.00496  -0.0101   0.8168   0.1209
  -3.500  -0.3518   0.01315   0.00467  -0.0095   0.8122   0.1705
  -3.250  -0.3291   0.01257   0.00440  -0.0089   0.8073   0.2345
  -3.000  -0.3076   0.01195   0.00416  -0.0081   0.8027   0.3221
  -2.750  -0.2846   0.01149   0.00396  -0.0073   0.7985   0.3913
  -2.500  -0.2624   0.01100   0.00385  -0.0063   0.7935   0.4639
  -2.250  -0.2396   0.01072   0.00395  -0.0052   0.7893   0.5586
  -2.000  -0.2141   0.01068   0.00403  -0.0044   0.7855   0.6081
  -1.750  -0.1881   0.01068   0.00414  -0.0037   0.7806   0.6423
  -1.500  -0.1618   0.01072   0.00425  -0.0030   0.7746   0.6649
  -1.250  -0.1354   0.01080   0.00434  -0.0023   0.7696   0.6849
  -1.000  -0.1089   0.01090   0.00448  -0.0017   0.7639   0.7046
  -0.750  -0.0822   0.01100   0.00460  -0.0011   0.7586   0.7197
  -0.500  -0.0551   0.01107   0.00467  -0.0005   0.7542   0.7293
  -0.250  -0.0276   0.01109   0.00467  -0.0003   0.7484   0.7375
   0.000   0.0000   0.01109   0.00470   0.0000   0.7425   0.7425
   0.250   0.0276   0.01109   0.00467   0.0003   0.7376   0.7484
   0.500   0.0551   0.01107   0.00467   0.0005   0.7293   0.7543
   0.750   0.0822   0.01100   0.00460   0.0011   0.7197   0.7586
   1.000   0.1089   0.01090   0.00448   0.0017   0.7048   0.7638
   1.250   0.1354   0.01080   0.00434   0.0023   0.6847   0.7696
   1.500   0.1618   0.01072   0.00425   0.0030   0.6649   0.7747
   1.750   0.1881   0.01068   0.00414   0.0037   0.6425   0.7806
   2.000   0.2141   0.01068   0.00403   0.0044   0.6085   0.7855
   2.250   0.2396   0.01072   0.00395   0.0052   0.5586   0.7893
   2.500   0.2624   0.01100   0.00385   0.0064   0.4637   0.7935
   2.750   0.2846   0.01150   0.00396   0.0073   0.3911   0.7985
   3.000   0.3076   0.01195   0.00416   0.0081   0.3222   0.8027
   3.250   0.3291   0.01257   0.00440   0.0089   0.2346   0.8073
   3.500   0.3518   0.01315   0.00467   0.0095   0.1708   0.8122
   3.750   0.3748   0.01369   0.00496   0.0101   0.1211   0.8168
   4.000   0.3988   0.01408   0.00525   0.0107   0.1000   0.8212
   4.250   0.4232   0.01444   0.00554   0.0112   0.0899   0.8263
   4.500   0.4483   0.01473   0.00585   0.0117   0.0841   0.8316
   4.750   0.4723   0.01507   0.00619   0.0124   0.0802   0.8369
   5.000   0.4966   0.01540   0.00655   0.0129   0.0774   0.8430
   5.250   0.5210   0.01572   0.00693   0.0135   0.0750   0.8489
   5.500   0.5451   0.01607   0.00732   0.0141   0.0728   0.8552
   6.000   0.5914   0.01705   0.00832   0.0154   0.0692   0.8698
   6.250   0.6159   0.01744   0.00878   0.0159   0.0678   0.8789
   6.500   0.6409   0.01785   0.00928   0.0163   0.0660   0.8898
   6.750   0.6670   0.01832   0.00982   0.0164   0.0643   0.9034
   7.000   0.6961   0.01887   0.01043   0.0159   0.0628   0.9208
   7.500   0.7640   0.02050   0.01206   0.0123   0.0601   0.9814
   7.750   0.7897   0.02122   0.01282   0.0123   0.0593   1.0000
   8.000   0.8125   0.02190   0.01356   0.0129   0.0585   1.0000
   8.250   0.8353   0.02262   0.01435   0.0135   0.0576   1.0000
   8.500   0.8578   0.02336   0.01516   0.0141   0.0565   1.0000
   8.750   0.8801   0.02410   0.01595   0.0147   0.0553   1.0000
   9.000   0.9021   0.02484   0.01676   0.0153   0.0542   1.0000
   9.250   0.9238   0.02565   0.01760   0.0159   0.0532   1.0000
   9.500   0.9455   0.02655   0.01853   0.0165   0.0525   1.0000
   9.750   0.9670   0.02760   0.01960   0.0170   0.0517   1.0000
  10.000   0.9882   0.02902   0.02106   0.0175   0.0509   1.0000
  10.250   1.0070   0.03002   0.02228   0.0184   0.0503   1.0000
  10.500   1.0244   0.03111   0.02358   0.0195   0.0495   1.0000
  10.750   1.0405   0.03229   0.02496   0.0206   0.0484   1.0000
  11.000   1.0554   0.03356   0.02642   0.0218   0.0474   1.0000
  11.250   1.0689   0.03492   0.02796   0.0230   0.0466   1.0000
  11.500   1.0808   0.03623   0.02943   0.0244   0.0457   1.0000
  11.750   1.0912   0.03747   0.03081   0.0258   0.0449   1.0000
  12.000   1.0994   0.03859   0.03204   0.0276   0.0442   1.0000
  12.250   1.1070   0.03961   0.03311   0.0294   0.0436   1.0000
  12.500   1.1145   0.04077   0.03431   0.0309   0.0429   1.0000
  12.750   1.1193   0.04252   0.03613   0.0322   0.0423   1.0000
  13.000   1.1143   0.04470   0.03852   0.0339   0.0418   1.0000
  13.250   1.1051   0.04725   0.04133   0.0351   0.0414   1.0000
  13.500   1.0923   0.05036   0.04472   0.0358   0.0408   1.0000
  13.750   1.0759   0.05419   0.04881   0.0357   0.0403   1.0000
  14.000   1.0553   0.05887   0.05375   0.0346   0.0399   1.0000
  14.250   1.0284   0.06483   0.05998   0.0322   0.0396   1.0000
  14.500   0.9907   0.07325   0.06867   0.0274   0.0395   1.0000
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