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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 200,000
Max Cl/Cd: 86.76 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e66-il-200000-n5.txt
Download as CSV file: xf-e66-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2983   0.13441   0.13101  -0.0369   1.0000   0.0243
 -11.250  -0.3771   0.12624   0.12252  -0.0372   1.0000   0.0179
 -11.000  -0.3717   0.12385   0.12014  -0.0361   1.0000   0.0170
 -10.750  -0.3711   0.12083   0.11716  -0.0360   1.0000   0.0162
 -10.500  -0.3726   0.11745   0.11381  -0.0360   1.0000   0.0155
 -10.000  -0.3888   0.10703   0.10348  -0.0375   1.0000   0.0131
  -9.750  -0.3928   0.10392   0.10042  -0.0371   1.0000   0.0130
  -9.500  -0.3983   0.10076   0.09731  -0.0367   1.0000   0.0129
  -9.250  -0.3995   0.09711   0.09369  -0.0377   0.9993   0.0128
  -9.000  -0.3921   0.09198   0.08858  -0.0421   0.9966   0.0127
  -8.750  -0.3863   0.08643   0.08305  -0.0471   0.9936   0.0126
  -8.500  -0.3824   0.08089   0.07753  -0.0520   0.9892   0.0125
  -8.250  -0.3833   0.07316   0.06984  -0.0596   0.9841   0.0125
  -8.000  -0.3882   0.06583   0.06255  -0.0668   0.9750   0.0123
  -7.750  -0.4002   0.03967   0.03571  -0.0986   0.9605   0.0116
  -7.500  -0.3883   0.03239   0.02763  -0.1039   0.9530   0.0119
  -7.250  -0.3628   0.02789   0.02242  -0.1073   0.9493   0.0123
  -7.000  -0.3319   0.02494   0.01884  -0.1098   0.9472   0.0130
  -6.750  -0.3065   0.02341   0.01712  -0.1106   0.9431   0.0142
  -6.500  -0.2794   0.02242   0.01597  -0.1113   0.9389   0.0155
  -6.250  -0.2483   0.02090   0.01416  -0.1126   0.9363   0.0167
  -6.000  -0.2153   0.01952   0.01252  -0.1140   0.9344   0.0179
  -5.750  -0.1816   0.01820   0.01106  -0.1159   0.9329   0.0197
  -5.500  -0.1579   0.01757   0.01034  -0.1154   0.9271   0.0223
  -5.250  -0.1268   0.01676   0.00941  -0.1164   0.9239   0.0261
  -5.000  -0.0933   0.01609   0.00866  -0.1178   0.9217   0.0305
  -4.750  -0.0585   0.01539   0.00790  -0.1195   0.9199   0.0369
  -4.500  -0.0287   0.01493   0.00734  -0.1200   0.9161   0.0440
  -4.250   0.0000   0.01442   0.00680  -0.1203   0.9114   0.0554
  -4.000   0.0336   0.01389   0.00630  -0.1217   0.9087   0.0724
  -3.750   0.0691   0.01344   0.00589  -0.1235   0.9066   0.0976
  -3.500   0.1060   0.01302   0.00551  -0.1255   0.9048   0.1266
  -3.250   0.1300   0.01275   0.00534  -0.1249   0.8977   0.1592
  -3.000   0.1640   0.01239   0.00508  -0.1263   0.8944   0.1990
  -2.750   0.2000   0.01205   0.00480  -0.1281   0.8918   0.2377
  -2.500   0.2281   0.01182   0.00466  -0.1282   0.8858   0.2746
  -2.250   0.2599   0.01156   0.00448  -0.1291   0.8809   0.3165
  -2.000   0.2954   0.01125   0.00428  -0.1307   0.8775   0.3665
  -1.750   0.3230   0.01107   0.00421  -0.1307   0.8708   0.4125
  -1.500   0.3552   0.01084   0.00410  -0.1316   0.8655   0.4625
  -1.250   0.3877   0.01062   0.00399  -0.1325   0.8604   0.5123
  -1.000   0.4154   0.01047   0.00397  -0.1324   0.8529   0.5597
  -0.750   0.4492   0.01026   0.00386  -0.1334   0.8481   0.6099
  -0.500   0.4741   0.01017   0.00390  -0.1327   0.8392   0.6544
  -0.250   0.5048   0.01002   0.00383  -0.1330   0.8328   0.6999
   0.000   0.5297   0.00994   0.00385  -0.1321   0.8237   0.7421
   0.250   0.5557   0.00984   0.00383  -0.1313   0.8153   0.7849
   0.500   0.5812   0.00974   0.00379  -0.1304   0.8066   0.8274
   0.750   0.6031   0.00967   0.00377  -0.1287   0.7962   0.8721
   1.000   0.6280   0.00957   0.00370  -0.1276   0.7864   0.9247
   1.250   0.6638   0.00949   0.00358  -0.1291   0.7765   1.0000
   1.500   0.6918   0.00956   0.00360  -0.1291   0.7648   1.0000
   1.750   0.7199   0.00963   0.00362  -0.1292   0.7527   1.0000
   2.000   0.7480   0.00972   0.00365  -0.1291   0.7399   1.0000
   2.250   0.7757   0.00982   0.00371  -0.1291   0.7262   1.0000
   2.500   0.8030   0.00993   0.00377  -0.1289   0.7116   1.0000
   2.750   0.8299   0.01006   0.00384  -0.1286   0.6958   1.0000
   3.000   0.8563   0.01021   0.00395  -0.1282   0.6793   1.0000
   3.250   0.8824   0.01038   0.00405  -0.1278   0.6618   1.0000
   3.500   0.9074   0.01057   0.00420  -0.1272   0.6425   1.0000
   3.750   0.9322   0.01078   0.00434  -0.1265   0.6220   1.0000
   4.000   0.9561   0.01102   0.00454  -0.1257   0.5997   1.0000
   4.250   0.9793   0.01130   0.00473  -0.1247   0.5755   1.0000
   4.500   1.0018   0.01159   0.00495  -0.1236   0.5496   1.0000
   4.750   1.0235   0.01193   0.00520  -0.1224   0.5221   1.0000
   5.000   1.0444   0.01231   0.00550  -0.1210   0.4932   1.0000
   5.250   1.0643   0.01274   0.00582  -0.1195   0.4625   1.0000
   5.500   1.0832   0.01321   0.00617  -0.1179   0.4300   1.0000
   5.750   1.1016   0.01373   0.00656  -0.1161   0.3958   1.0000
   6.000   1.1186   0.01431   0.00700  -0.1143   0.3601   1.0000
   6.250   1.1355   0.01492   0.00750  -0.1124   0.3247   1.0000
   6.500   1.1521   0.01556   0.00801  -0.1105   0.2912   1.0000
   6.750   1.1685   0.01622   0.00855  -0.1086   0.2607   1.0000
   7.000   1.1838   0.01690   0.00913  -0.1066   0.2310   1.0000
   7.250   1.1981   0.01765   0.00974  -0.1044   0.2004   1.0000
   7.500   1.2114   0.01849   0.01043  -0.1021   0.1674   1.0000
   7.750   1.2244   0.01938   0.01118  -0.0999   0.1373   1.0000
   8.000   1.2382   0.02023   0.01194  -0.0978   0.1140   1.0000
   8.250   1.2523   0.02107   0.01272  -0.0959   0.0958   1.0000
   8.500   1.2658   0.02196   0.01356  -0.0938   0.0797   1.0000
   8.750   1.2794   0.02285   0.01443  -0.0918   0.0659   1.0000
   9.000   1.2922   0.02380   0.01538  -0.0898   0.0548   1.0000
   9.500   1.3157   0.02588   0.01754  -0.0855   0.0381   1.0000
   9.750   1.3261   0.02705   0.01876  -0.0833   0.0326   1.0000
  10.000   1.3358   0.02827   0.02003  -0.0811   0.0283   1.0000
  10.250   1.3435   0.02967   0.02152  -0.0788   0.0256   1.0000
  10.500   1.3530   0.03096   0.02294  -0.0767   0.0233   1.0000
  10.750   1.3614   0.03235   0.02442  -0.0747   0.0212   1.0000
  11.000   1.3645   0.03422   0.02636  -0.0724   0.0193   1.0000
  11.250   1.3723   0.03575   0.02804  -0.0706   0.0181   1.0000
  11.500   1.3791   0.03740   0.02985  -0.0688   0.0167   1.0000
  11.750   1.3853   0.03912   0.03169  -0.0672   0.0153   1.0000
  12.000   1.3873   0.04131   0.03397  -0.0655   0.0144   1.0000
  12.250   1.3857   0.04396   0.03674  -0.0637   0.0137   1.0000
  12.500   1.3888   0.04625   0.03922  -0.0623   0.0131   1.0000
  12.750   1.3905   0.04878   0.04192  -0.0611   0.0124   1.0000
  13.000   1.3915   0.05144   0.04475  -0.0601   0.0118   1.0000
  13.250   1.3922   0.05419   0.04764  -0.0593   0.0111   1.0000
  13.500   1.3919   0.05714   0.05072  -0.0588   0.0106   1.0000
  13.750   1.3892   0.06049   0.05420  -0.0585   0.0101   1.0000
  14.000   1.3817   0.06465   0.05846  -0.0585   0.0097   1.0000
  14.250   1.3803   0.06819   0.06223  -0.0586   0.0093   1.0000
  14.500   1.3771   0.07213   0.06639  -0.0590   0.0089   1.0000
  14.750   1.3718   0.07652   0.07102  -0.0598   0.0086   1.0000
  15.000   1.3654   0.08123   0.07593  -0.0608   0.0084   1.0000
  15.250   1.3581   0.08627   0.08117  -0.0623   0.0082   1.0000
  15.500   1.3497   0.09168   0.08677  -0.0642   0.0080   1.0000
  15.750   1.3404   0.09743   0.09272  -0.0665   0.0079   1.0000
  16.000   1.3304   0.10354   0.09903  -0.0692   0.0077   1.0000
  16.250   1.3197   0.11001   0.10568  -0.0724   0.0076   1.0000
  16.500   1.3083   0.11684   0.11270  -0.0760   0.0076   1.0000
  16.750   1.2963   0.12405   0.12009  -0.0801   0.0075   1.0000
  17.000   1.2834   0.13172   0.12795  -0.0846   0.0075   1.0000
  17.250   1.2696   0.13992   0.13634  -0.0897   0.0074   1.0000
  17.500   1.2546   0.14880   0.14540  -0.0954   0.0075   1.0000
  17.750   1.2375   0.15868   0.15548  -0.1018   0.0075   1.0000
  18.000   1.2156   0.17059   0.16758  -0.1097   0.0077   1.0000
  18.250   1.1812   0.18800   0.18516  -0.1208   0.0081   1.0000
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