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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 100,000
Max Cl/Cd: 63.7 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e66-il-100000-n5.txt
Download as CSV file: xf-e66-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4085   0.09315   0.08849  -0.0384   1.0000   0.0243
  -8.250  -0.4222   0.08968   0.08513  -0.0378   1.0000   0.0245
  -8.000  -0.4332   0.08733   0.08285  -0.0362   1.0000   0.0243
  -7.750  -0.4489   0.08488   0.08050  -0.0344   1.0000   0.0242
  -7.500  -0.4459   0.07899   0.07464  -0.0405   0.9948   0.0242
  -7.250  -0.4350   0.07178   0.06743  -0.0495   0.9880   0.0239
  -7.000  -0.4212   0.06039   0.05591  -0.0641   0.9805   0.0236
  -6.750  -0.4057   0.04917   0.04419  -0.0774   0.9732   0.0233
  -6.500  -0.3853   0.04120   0.03548  -0.0850   0.9673   0.0234
  -6.250  -0.3570   0.03541   0.02884  -0.0899   0.9631   0.0239
  -6.000  -0.3242   0.03139   0.02407  -0.0933   0.9604   0.0248
  -5.750  -0.2960   0.02955   0.02206  -0.0949   0.9565   0.0269
  -5.500  -0.2666   0.02801   0.02017  -0.0962   0.9522   0.0304
  -5.250  -0.2330   0.02608   0.01773  -0.0977   0.9492   0.0330
  -5.000  -0.1990   0.02461   0.01618  -0.0998   0.9468   0.0375
  -4.750  -0.1714   0.02366   0.01497  -0.1000   0.9418   0.0430
  -4.500  -0.1403   0.02258   0.01384  -0.1012   0.9377   0.0492
  -4.250  -0.1060   0.02168   0.01279  -0.1027   0.9347   0.0586
  -4.000  -0.0721   0.02088   0.01192  -0.1042   0.9315   0.0710
  -3.750  -0.0447   0.02030   0.01135  -0.1045   0.9256   0.0902
  -3.500  -0.0109   0.01972   0.01081  -0.1061   0.9219   0.1189
  -3.250   0.0255   0.01921   0.01038  -0.1081   0.9192   0.1600
  -3.000   0.0512   0.01889   0.01013  -0.1080   0.9125   0.1977
  -2.750   0.0844   0.01851   0.00985  -0.1094   0.9083   0.2437
  -2.500   0.1207   0.01813   0.00957  -0.1112   0.9054   0.2968
  -2.250   0.1458   0.01792   0.00947  -0.1109   0.8982   0.3458
  -2.000   0.1789   0.01761   0.00930  -0.1120   0.8939   0.4060
  -1.750   0.2150   0.01727   0.00911  -0.1135   0.8910   0.4712
  -1.500   0.2383   0.01716   0.00912  -0.1126   0.8831   0.5276
  -1.250   0.2715   0.01688   0.00898  -0.1134   0.8791   0.5928
  -1.000   0.3016   0.01665   0.00888  -0.1134   0.8744   0.6557
  -0.750   0.3255   0.01650   0.00886  -0.1122   0.8671   0.7146
  -0.500   0.3560   0.01620   0.00866  -0.1119   0.8634   0.7783
  -0.250   0.3733   0.01608   0.00864  -0.1092   0.8547   0.8422
   0.000   0.4077   0.01571   0.00831  -0.1098   0.8503   0.9463
   0.250   0.4395   0.01566   0.00816  -0.1107   0.8427   1.0000
   0.500   0.4750   0.01560   0.00799  -0.1122   0.8370   1.0000
   0.750   0.5084   0.01557   0.00787  -0.1133   0.8305   1.0000
   1.000   0.5404   0.01554   0.00778  -0.1140   0.8231   1.0000
   1.250   0.5728   0.01551   0.00769  -0.1148   0.8158   1.0000
   1.500   0.6058   0.01545   0.00758  -0.1157   0.8081   1.0000
   1.750   0.6352   0.01546   0.00758  -0.1159   0.7988   1.0000
   2.000   0.6719   0.01532   0.00741  -0.1173   0.7918   1.0000
   2.250   0.6990   0.01538   0.00746  -0.1171   0.7807   1.0000
   2.500   0.7292   0.01538   0.00748  -0.1173   0.7703   1.0000
   2.750   0.7622   0.01532   0.00742  -0.1181   0.7602   1.0000
   3.000   0.7940   0.01528   0.00738  -0.1186   0.7488   1.0000
   3.250   0.8226   0.01532   0.00746  -0.1185   0.7354   1.0000
   3.500   0.8516   0.01536   0.00752  -0.1185   0.7213   1.0000
   3.750   0.8810   0.01540   0.00757  -0.1185   0.7063   1.0000
   4.000   0.9093   0.01547   0.00766  -0.1184   0.6898   1.0000
   4.250   0.9355   0.01560   0.00784  -0.1178   0.6715   1.0000
   4.500   0.9624   0.01573   0.00798  -0.1174   0.6522   1.0000
   4.750   0.9891   0.01588   0.00813  -0.1169   0.6315   1.0000
   5.000   1.0136   0.01610   0.00835  -0.1160   0.6081   1.0000
   5.250   1.0375   0.01635   0.00862  -0.1150   0.5830   1.0000
   5.500   1.0606   0.01665   0.00888  -0.1139   0.5557   1.0000
   5.750   1.0824   0.01701   0.00920  -0.1126   0.5263   1.0000
   6.000   1.1029   0.01743   0.00956  -0.1111   0.4947   1.0000
   6.250   1.1220   0.01793   0.01001  -0.1094   0.4615   1.0000
   6.500   1.1396   0.01850   0.01049  -0.1075   0.4260   1.0000
   6.750   1.1555   0.01917   0.01103  -0.1054   0.3893   1.0000
   7.000   1.1703   0.01990   0.01165  -0.1031   0.3518   1.0000
   7.250   1.1835   0.02072   0.01233  -0.1008   0.3151   1.0000
   7.500   1.1961   0.02158   0.01308  -0.0983   0.2796   1.0000
   7.750   1.2072   0.02250   0.01392  -0.0957   0.2468   1.0000
   8.000   1.2180   0.02350   0.01481  -0.0931   0.2163   1.0000
   8.250   1.2285   0.02457   0.01578  -0.0906   0.1863   1.0000
   8.500   1.2383   0.02573   0.01682  -0.0882   0.1578   1.0000
   8.750   1.2474   0.02697   0.01795  -0.0857   0.1313   1.0000
   9.000   1.2564   0.02826   0.01916  -0.0833   0.1086   1.0000
   9.250   1.2653   0.02960   0.02045  -0.0810   0.0909   1.0000
   9.500   1.2737   0.03100   0.02186  -0.0787   0.0767   1.0000
   9.750   1.2806   0.03254   0.02346  -0.0763   0.0656   1.0000
  10.000   1.2856   0.03426   0.02515  -0.0739   0.0564   1.0000
  10.250   1.2926   0.03588   0.02692  -0.0717   0.0490   1.0000
  10.500   1.2947   0.03793   0.02900  -0.0693   0.0447   1.0000
  10.750   1.2999   0.03983   0.03109  -0.0671   0.0407   1.0000
  11.000   1.3038   0.04186   0.03323  -0.0652   0.0374   1.0000
  11.250   1.3047   0.04425   0.03568  -0.0632   0.0346   1.0000
  11.500   1.3105   0.04635   0.03800  -0.0616   0.0319   1.0000
  11.750   1.3144   0.04870   0.04052  -0.0600   0.0300   1.0000
  12.000   1.3171   0.05115   0.04313  -0.0587   0.0283   1.0000
  12.250   1.3172   0.05401   0.04605  -0.0575   0.0267   1.0000
  12.500   1.3210   0.05669   0.04898  -0.0564   0.0250   1.0000
  12.750   1.3237   0.05954   0.05207  -0.0554   0.0235   1.0000
  13.000   1.3249   0.06265   0.05541  -0.0546   0.0225   1.0000
  13.250   1.3239   0.06592   0.05885  -0.0541   0.0214   1.0000
  13.500   1.3213   0.06936   0.06243  -0.0539   0.0205   1.0000
  13.750   1.3171   0.07315   0.06634  -0.0540   0.0197   1.0000
  14.000   1.3108   0.07754   0.07094  -0.0542   0.0190   1.0000
  14.250   1.3031   0.08224   0.07596  -0.0550   0.0184   1.0000
  14.500   1.2936   0.08740   0.08142  -0.0562   0.0179   1.0000
  14.750   1.2823   0.09306   0.08735  -0.0580   0.0175   1.0000
  15.000   1.2694   0.09926   0.09382  -0.0604   0.0173   1.0000
  15.250   1.2547   0.10609   0.10090  -0.0636   0.0172   1.0000
  15.500   1.2386   0.11357   0.10863  -0.0676   0.0171   1.0000
  15.750   1.2209   0.12183   0.11712  -0.0725   0.0172   1.0000
  16.000   1.2018   0.13103   0.12654  -0.0783   0.0173   1.0000
  16.250   1.1810   0.14135   0.13706  -0.0852   0.0175   1.0000
  16.500   1.1587   0.15301   0.14887  -0.0931   0.0179   1.0000
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