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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 1,000,000
Max Cl/Cd: 153.17 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e66-il-1000000.txt
Download as CSV file: xf-e66-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3599   0.11177   0.11013  -0.0411   0.9970   0.0108
 -10.250  -0.3517   0.10517   0.10354  -0.0464   0.9959   0.0119
  -9.250  -0.4682   0.02535   0.02249  -0.1245   0.9726   0.0070
  -9.000  -0.4531   0.02262   0.01944  -0.1251   0.9668   0.0070
  -8.750  -0.4273   0.02009   0.01658  -0.1271   0.9642   0.0071
  -8.500  -0.3974   0.01836   0.01463  -0.1291   0.9627   0.0073
  -8.250  -0.3654   0.01723   0.01332  -0.1309   0.9617   0.0077
  -8.000  -0.3329   0.01592   0.01182  -0.1328   0.9609   0.0080
  -7.750  -0.2998   0.01467   0.01038  -0.1346   0.9602   0.0083
  -7.500  -0.2656   0.01377   0.00934  -0.1365   0.9596   0.0085
  -7.250  -0.2456   0.01235   0.00772  -0.1355   0.9540   0.0090
  -7.000  -0.2145   0.01162   0.00692  -0.1366   0.9518   0.0097
  -6.750  -0.1817   0.01109   0.00634  -0.1379   0.9501   0.0104
  -6.500  -0.1485   0.01057   0.00575  -0.1393   0.9484   0.0111
  -6.250  -0.1146   0.01015   0.00527  -0.1407   0.9469   0.0118
  -6.000  -0.0863   0.00941   0.00445  -0.1411   0.9428   0.0134
  -5.750  -0.0571   0.00910   0.00410  -0.1415   0.9386   0.0150
  -5.500  -0.0250   0.00871   0.00365  -0.1425   0.9354   0.0173
  -5.250   0.0091   0.00833   0.00325  -0.1440   0.9326   0.0207
  -5.000   0.0356   0.00804   0.00290  -0.1437   0.9266   0.0239
  -4.750   0.0662   0.00775   0.00260  -0.1443   0.9218   0.0285
  -4.500   0.0977   0.00746   0.00231  -0.1452   0.9173   0.0386
  -4.250   0.1245   0.00718   0.00211  -0.1451   0.9107   0.0601
  -4.000   0.1552   0.00695   0.00192  -0.1458   0.9055   0.0805
  -3.750   0.1827   0.00677   0.00179  -0.1457   0.8990   0.1011
  -3.500   0.2116   0.00659   0.00165  -0.1460   0.8928   0.1243
  -3.250   0.2400   0.00644   0.00154  -0.1462   0.8864   0.1485
  -3.000   0.2680   0.00629   0.00144  -0.1463   0.8795   0.1777
  -2.750   0.2963   0.00614   0.00136  -0.1464   0.8730   0.2107
  -2.500   0.3240   0.00598   0.00130  -0.1464   0.8656   0.2496
  -2.250   0.3520   0.00585   0.00123  -0.1465   0.8586   0.2860
  -2.000   0.3797   0.00575   0.00119  -0.1465   0.8507   0.3220
  -1.750   0.4074   0.00565   0.00115  -0.1465   0.8429   0.3552
  -1.500   0.4350   0.00557   0.00112  -0.1465   0.8344   0.3919
  -1.250   0.4624   0.00547   0.00111  -0.1464   0.8256   0.4334
  -1.000   0.4899   0.00540   0.00110  -0.1463   0.8169   0.4753
  -0.750   0.5171   0.00534   0.00111  -0.1462   0.8073   0.5159
  -0.500   0.5443   0.00528   0.00112  -0.1460   0.7978   0.5554
  -0.250   0.5713   0.00525   0.00114  -0.1458   0.7878   0.5936
   0.000   0.5981   0.00523   0.00117  -0.1456   0.7769   0.6316
   0.250   0.6248   0.00520   0.00121  -0.1453   0.7656   0.6693
   0.500   0.6512   0.00520   0.00126  -0.1449   0.7537   0.7058
   0.750   0.6774   0.00521   0.00131  -0.1445   0.7410   0.7405
   1.000   0.7031   0.00523   0.00137  -0.1440   0.7279   0.7741
   1.250   0.7284   0.00526   0.00144  -0.1433   0.7141   0.8067
   1.500   0.7530   0.00531   0.00151  -0.1425   0.6997   0.8391
   1.750   0.7768   0.00536   0.00159  -0.1415   0.6847   0.8718
   2.000   0.7988   0.00540   0.00167  -0.1401   0.6688   0.9051
   2.250   0.8182   0.00543   0.00171  -0.1381   0.6522   0.9456
   2.500   0.8455   0.00552   0.00175  -0.1379   0.6331   1.0000
   2.750   0.8710   0.00570   0.00184  -0.1375   0.6133   1.0000
   3.000   0.8963   0.00588   0.00195  -0.1370   0.5921   1.0000
   3.250   0.9211   0.00609   0.00207  -0.1364   0.5701   1.0000
   3.500   0.9457   0.00631   0.00219  -0.1357   0.5463   1.0000
   3.750   0.9702   0.00655   0.00234  -0.1351   0.5218   1.0000
   4.000   0.9939   0.00683   0.00251  -0.1343   0.4940   1.0000
   4.250   1.0170   0.00715   0.00269  -0.1335   0.4615   1.0000
   4.500   1.0400   0.00749   0.00290  -0.1326   0.4297   1.0000
   4.750   1.0625   0.00787   0.00313  -0.1316   0.3961   1.0000
   5.000   1.0853   0.00823   0.00336  -0.1308   0.3649   1.0000
   5.250   1.1076   0.00864   0.00362  -0.1298   0.3317   1.0000
   5.500   1.1283   0.00915   0.00393  -0.1286   0.2912   1.0000
   5.750   1.1486   0.00969   0.00428  -0.1273   0.2506   1.0000
   6.000   1.1690   0.01022   0.00462  -0.1261   0.2143   1.0000
   6.250   1.1894   0.01074   0.00499  -0.1248   0.1830   1.0000
   6.500   1.2103   0.01122   0.00534  -0.1237   0.1572   1.0000
   6.750   1.2309   0.01170   0.00572  -0.1225   0.1336   1.0000
   7.000   1.2507   0.01223   0.00612  -0.1211   0.1110   1.0000
   7.250   1.2703   0.01276   0.00655  -0.1198   0.0908   1.0000
   7.500   1.2897   0.01327   0.00697  -0.1184   0.0743   1.0000
   7.750   1.3081   0.01378   0.00741  -0.1167   0.0597   1.0000
   8.000   1.3255   0.01431   0.00787  -0.1150   0.0469   1.0000
   8.250   1.3416   0.01491   0.00841  -0.1129   0.0345   1.0000
   8.500   1.3566   0.01558   0.00901  -0.1108   0.0237   1.0000
   8.750   1.3730   0.01617   0.00957  -0.1089   0.0191   1.0000
   9.000   1.3893   0.01675   0.01019  -0.1069   0.0164   1.0000
   9.250   1.4061   0.01729   0.01075  -0.1051   0.0147   1.0000
   9.500   1.4200   0.01804   0.01152  -0.1029   0.0126   1.0000
   9.750   1.4361   0.01861   0.01217  -0.1010   0.0118   1.0000
  10.000   1.4521   0.01920   0.01280  -0.0992   0.0110   1.0000
  10.250   1.4668   0.01987   0.01352  -0.0973   0.0101   1.0000
  10.500   1.4763   0.02092   0.01463  -0.0946   0.0090   1.0000
  10.750   1.4889   0.02174   0.01552  -0.0924   0.0085   1.0000
  11.000   1.5030   0.02246   0.01631  -0.0906   0.0079   1.0000
  11.250   1.5159   0.02327   0.01717  -0.0886   0.0074   1.0000
  11.500   1.5275   0.02418   0.01814  -0.0866   0.0069   1.0000
  11.750   1.5345   0.02546   0.01950  -0.0840   0.0064   1.0000
  12.000   1.5346   0.02730   0.02147  -0.0808   0.0060   1.0000
  12.250   1.5463   0.02828   0.02252  -0.0791   0.0058   1.0000
  12.500   1.5571   0.02935   0.02367  -0.0773   0.0055   1.0000
  12.750   1.5660   0.03060   0.02500  -0.0755   0.0052   1.0000
  13.000   1.5748   0.03189   0.02636  -0.0738   0.0050   1.0000
  13.250   1.5830   0.03327   0.02780  -0.0722   0.0047   1.0000
  13.500   1.5887   0.03490   0.02951  -0.0705   0.0046   1.0000
  13.750   1.5908   0.03693   0.03163  -0.0687   0.0044   1.0000
  14.000   1.5829   0.04002   0.03487  -0.0665   0.0041   1.0000
  14.250   1.5708   0.04375   0.03876  -0.0645   0.0040   1.0000
  14.500   1.5733   0.04609   0.04123  -0.0636   0.0039   1.0000
  14.750   1.5735   0.04880   0.04406  -0.0627   0.0039   1.0000
  15.000   1.5739   0.05159   0.04696  -0.0621   0.0038   1.0000
  15.250   1.5723   0.05476   0.05025  -0.0618   0.0037   1.0000
  15.500   1.5681   0.05842   0.05404  -0.0617   0.0037   1.0000
  15.750   1.5632   0.06235   0.05810  -0.0619   0.0036   1.0000
  16.000   1.5575   0.06657   0.06245  -0.0625   0.0036   1.0000
  16.250   1.5501   0.07125   0.06728  -0.0634   0.0035   1.0000
  16.500   1.5416   0.07632   0.07248  -0.0648   0.0035   1.0000
  16.750   1.5316   0.08183   0.07814  -0.0665   0.0034   1.0000
  17.000   1.5212   0.08765   0.08410  -0.0687   0.0034   1.0000
  17.250   1.5094   0.09397   0.09056  -0.0713   0.0034   1.0000
  17.500   1.4971   0.10058   0.09732  -0.0743   0.0033   1.0000
  17.750   1.4826   0.10781   0.10469  -0.0778   0.0033   1.0000
  18.000   1.4687   0.11514   0.11217  -0.0815   0.0033   1.0000
  18.250   1.4535   0.12292   0.12009  -0.0857   0.0033   1.0000
  18.500   1.4386   0.13079   0.12810  -0.0901   0.0033   1.0000
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