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EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EA 6(-1)-012 AIRFOIL (ea61012-il)
Reynolds number: 500,000
Max Cl/Cd: 47.09 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ea61012-il-500000.txt
Download as CSV file: xf-ea61012-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -1.0861   0.09449   0.09148  -0.0144   1.0000   0.0300
 -17.000  -1.1439   0.07945   0.07612  -0.0245   1.0000   0.0299
 -16.750  -1.1711   0.07116   0.06761  -0.0297   1.0000   0.0301
 -16.500  -1.1917   0.06473   0.06097  -0.0333   1.0000   0.0304
 -16.250  -1.2083   0.05946   0.05550  -0.0359   1.0000   0.0308
 -16.000  -1.2213   0.05510   0.05093  -0.0376   1.0000   0.0311
 -15.750  -1.2330   0.05111   0.04675  -0.0387   1.0000   0.0314
 -15.500  -1.2373   0.04807   0.04365  -0.0390   1.0000   0.0320
 -15.250  -1.2325   0.04628   0.04184  -0.0390   1.0000   0.0324
 -15.000  -1.2257   0.04486   0.04041  -0.0390   1.0000   0.0328
 -14.750  -1.2212   0.04327   0.03877  -0.0388   1.0000   0.0333
 -14.500  -1.2181   0.04164   0.03705  -0.0384   1.0000   0.0338
 -14.250  -1.2160   0.04000   0.03531  -0.0377   1.0000   0.0344
 -14.000  -1.2148   0.03822   0.03341  -0.0367   1.0000   0.0350
 -13.750  -1.2134   0.03673   0.03176  -0.0355   1.0000   0.0357
 -13.500  -1.2123   0.03535   0.03021  -0.0339   1.0000   0.0362
 -13.250  -1.2120   0.03417   0.02887  -0.0319   1.0000   0.0367
 -13.000  -1.2039   0.03225   0.02690  -0.0305   1.0000   0.0375
 -12.750  -1.1934   0.03168   0.02633  -0.0289   1.0000   0.0381
 -12.500  -1.1842   0.03114   0.02577  -0.0267   1.0000   0.0387
 -12.250  -1.1741   0.03051   0.02508  -0.0247   1.0000   0.0393
 -12.000  -1.1604   0.02982   0.02433  -0.0232   1.0000   0.0401
 -11.750  -1.1457   0.02910   0.02351  -0.0218   1.0000   0.0410
 -11.500  -1.1306   0.02843   0.02270  -0.0204   1.0000   0.0419
 -11.250  -1.1147   0.02800   0.02213  -0.0189   1.0000   0.0426
 -11.000  -1.0973   0.02605   0.02008  -0.0182   1.0000   0.0437
 -10.750  -1.0770   0.02527   0.01932  -0.0175   1.0000   0.0446
 -10.500  -1.0568   0.02469   0.01871  -0.0167   1.0000   0.0454
 -10.250  -1.0364   0.02415   0.01813  -0.0159   1.0000   0.0464
 -10.000  -1.0152   0.02353   0.01744  -0.0151   1.0000   0.0474
  -9.750  -0.9936   0.02285   0.01669  -0.0144   1.0000   0.0483
  -9.500  -0.9717   0.02231   0.01605  -0.0136   1.0000   0.0492
  -9.250  -0.9494   0.02193   0.01559  -0.0129   1.0000   0.0499
  -9.000  -0.9269   0.02024   0.01384  -0.0125   1.0000   0.0510
  -8.750  -0.9041   0.01935   0.01297  -0.0120   1.0000   0.0520
  -8.500  -0.8810   0.01877   0.01240  -0.0115   1.0000   0.0530
  -8.250  -0.8577   0.01825   0.01188  -0.0109   1.0000   0.0541
  -8.000  -0.8310   0.01766   0.01127  -0.0111   0.9878   0.0552
  -7.750  -0.7879   0.01696   0.01050  -0.0146   0.9477   0.0565
  -7.500  -0.7524   0.01645   0.00989  -0.0164   0.9191   0.0575
  -7.250  -0.7267   0.01619   0.00950  -0.0161   0.8992   0.0583
  -7.000  -0.7057   0.01527   0.00850  -0.0150   0.8861   0.0598
  -6.750  -0.6836   0.01469   0.00789  -0.0141   0.8760   0.0610
  -6.500  -0.6604   0.01429   0.00745  -0.0134   0.8681   0.0623
  -6.250  -0.6365   0.01392   0.00705  -0.0127   0.8608   0.0636
  -5.750  -0.5875   0.01332   0.00634  -0.0115   0.8482   0.0666
  -5.500  -0.5624   0.01307   0.00604  -0.0110   0.8422   0.0678
  -5.250  -0.5390   0.01264   0.00556  -0.0102   0.8370   0.0695
  -5.000  -0.5149   0.01220   0.00513  -0.0096   0.8316   0.0718
  -4.750  -0.4897   0.01192   0.00483  -0.0091   0.8266   0.0742
  -4.500  -0.4641   0.01171   0.00458  -0.0087   0.8220   0.0768
  -4.250  -0.4376   0.01151   0.00436  -0.0084   0.8173   0.0793
  -4.000  -0.4126   0.01115   0.00403  -0.0079   0.8125   0.0850
  -3.750  -0.3866   0.01093   0.00380  -0.0075   0.8082   0.0912
  -3.500  -0.3617   0.01056   0.00355  -0.0070   0.8038   0.1118
  -3.250  -0.3400   0.00975   0.00322  -0.0062   0.7987   0.2076
  -3.000  -0.3195   0.00888   0.00291  -0.0053   0.7936   0.3392
  -2.750  -0.2967   0.00835   0.00269  -0.0045   0.7890   0.4247
  -2.500  -0.2751   0.00771   0.00259  -0.0034   0.7837   0.5457
  -2.250  -0.2488   0.00758   0.00258  -0.0029   0.7789   0.5939
  -2.000  -0.2217   0.00754   0.00257  -0.0025   0.7747   0.6205
  -1.750  -0.1941   0.00752   0.00258  -0.0023   0.7703   0.6404
  -1.500  -0.1664   0.00750   0.00260  -0.0020   0.7655   0.6577
  -1.250  -0.1388   0.00750   0.00263  -0.0017   0.7609   0.6747
  -1.000  -0.1110   0.00755   0.00267  -0.0014   0.7569   0.6889
  -0.750  -0.0830   0.00757   0.00274  -0.0012   0.7526   0.6991
  -0.500  -0.0550   0.00760   0.00279  -0.0009   0.7474   0.7109
  -0.250  -0.0274   0.00765   0.00280  -0.0005   0.7411   0.7220
   0.000   0.0000   0.00764   0.00284   0.0000   0.7316   0.7316
   0.250   0.0273   0.00765   0.00280   0.0005   0.7221   0.7410
   0.500   0.0550   0.00760   0.00279   0.0009   0.7109   0.7473
   0.750   0.0829   0.00757   0.00274   0.0012   0.6991   0.7526
   1.000   0.1110   0.00755   0.00266   0.0014   0.6888   0.7569
   1.250   0.1387   0.00750   0.00263   0.0017   0.6747   0.7609
   1.500   0.1663   0.00750   0.00260   0.0020   0.6578   0.7655
   1.750   0.1940   0.00752   0.00258   0.0023   0.6402   0.7703
   2.000   0.2217   0.00754   0.00257   0.0025   0.6204   0.7747
   2.250   0.2488   0.00758   0.00258   0.0029   0.5937   0.7789
   2.500   0.2751   0.00771   0.00259   0.0034   0.5459   0.7837
   2.750   0.2967   0.00834   0.00269   0.0045   0.4252   0.7890
   3.000   0.3195   0.00888   0.00291   0.0053   0.3392   0.7936
   3.250   0.3400   0.00975   0.00322   0.0062   0.2074   0.7987
   3.500   0.3616   0.01056   0.00355   0.0070   0.1116   0.8038
   3.750   0.3865   0.01093   0.00380   0.0075   0.0912   0.8082
   4.000   0.4125   0.01114   0.00403   0.0079   0.0851   0.8125
   4.250   0.4376   0.01151   0.00436   0.0084   0.0793   0.8174
   4.500   0.4641   0.01171   0.00457   0.0087   0.0768   0.8220
   4.750   0.4897   0.01191   0.00483   0.0092   0.0742   0.8266
   5.000   0.5148   0.01220   0.00513   0.0096   0.0718   0.8317
   5.250   0.5389   0.01264   0.00556   0.0103   0.0695   0.8370
   5.500   0.5624   0.01307   0.00604   0.0110   0.0678   0.8422
   5.750   0.5874   0.01331   0.00634   0.0115   0.0666   0.8482
   6.250   0.6364   0.01392   0.00704   0.0127   0.0636   0.8609
   6.500   0.6603   0.01428   0.00744   0.0134   0.0623   0.8682
   6.750   0.6836   0.01468   0.00788   0.0141   0.0611   0.8760
   7.000   0.7057   0.01526   0.00849   0.0150   0.0598   0.8861
   7.250   0.7266   0.01620   0.00951   0.0161   0.0583   0.8992
   7.500   0.7524   0.01644   0.00987   0.0165   0.0575   0.9193
   7.750   0.7880   0.01696   0.01050   0.0146   0.0565   0.9479
   8.000   0.8311   0.01765   0.01126   0.0111   0.0551   0.9884
   8.250   0.8577   0.01825   0.01188   0.0109   0.0541   1.0000
   8.500   0.8810   0.01877   0.01240   0.0115   0.0530   1.0000
   8.750   0.9041   0.01934   0.01296   0.0120   0.0520   1.0000
   9.000   0.9270   0.02023   0.01384   0.0125   0.0510   1.0000
   9.250   0.9494   0.02192   0.01558   0.0129   0.0499   1.0000
   9.500   0.9718   0.02230   0.01605   0.0136   0.0492   1.0000
   9.750   0.9937   0.02285   0.01668   0.0144   0.0483   1.0000
  10.000   1.0153   0.02352   0.01744   0.0151   0.0473   1.0000
  10.250   1.0365   0.02411   0.01808   0.0159   0.0463   1.0000
  10.500   1.0569   0.02469   0.01871   0.0167   0.0454   1.0000
  10.750   1.0771   0.02524   0.01928   0.0175   0.0445   1.0000
  11.000   1.0974   0.02606   0.02009   0.0182   0.0437   1.0000
  11.250   1.1148   0.02797   0.02210   0.0189   0.0426   1.0000
  11.500   1.1306   0.02843   0.02271   0.0204   0.0419   1.0000
  11.750   1.1458   0.02921   0.02362   0.0218   0.0411   1.0000
  12.000   1.1603   0.03000   0.02452   0.0232   0.0402   1.0000
  12.250   1.1743   0.03059   0.02517   0.0247   0.0393   1.0000
  12.500   1.1846   0.03114   0.02577   0.0267   0.0387   1.0000
  12.750   1.1939   0.03164   0.02629   0.0288   0.0381   1.0000
  13.000   1.2041   0.03233   0.02699   0.0305   0.0375   1.0000
  13.250   1.2116   0.03436   0.02906   0.0318   0.0366   1.0000
  13.500   1.2126   0.03542   0.03029   0.0339   0.0363   1.0000
  13.750   1.2141   0.03663   0.03167   0.0355   0.0356   1.0000
  14.000   1.2150   0.03828   0.03346   0.0367   0.0350   1.0000
  14.250   1.2175   0.03987   0.03517   0.0376   0.0344   1.0000
  14.500   1.2192   0.04161   0.03702   0.0382   0.0338   1.0000
  14.750   1.2222   0.04324   0.03874   0.0387   0.0333   1.0000
  15.000   1.2271   0.04479   0.04033   0.0389   0.0328   1.0000
  15.250   1.2318   0.04648   0.04207   0.0389   0.0324   1.0000
  15.500   1.2386   0.04802   0.04360   0.0389   0.0320   1.0000
  15.750   1.2351   0.05097   0.04661   0.0386   0.0315   1.0000
  16.000   1.2215   0.05521   0.05105   0.0375   0.0311   1.0000
  16.250   1.2086   0.05957   0.05561   0.0357   0.0308   1.0000
  16.500   1.1944   0.06450   0.06073   0.0332   0.0304   1.0000
  16.750   1.1753   0.07069   0.06713   0.0297   0.0300   1.0000
  17.000   1.1406   0.08025   0.07694   0.0238   0.0300   1.0000
  17.250   1.0703   0.09791   0.09496   0.0119   0.0304   1.0000
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