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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 200,000
Max Cl/Cd: 78.43 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e68-il-200000-n5.txt
Download as CSV file: xf-e68-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5776   0.07174   0.06786  -0.0686   1.0000   0.0141
 -11.750  -0.6127   0.06325   0.05920  -0.0734   1.0000   0.0138
 -11.500  -0.6392   0.05803   0.05390  -0.0751   1.0000   0.0138
 -11.250  -0.6575   0.05203   0.04772  -0.0803   0.9975   0.0138
 -11.000  -0.6635   0.04603   0.04139  -0.0882   0.9906   0.0138
 -10.750  -0.6645   0.04184   0.03688  -0.0930   0.9834   0.0138
 -10.500  -0.6632   0.03849   0.03322  -0.0943   0.9746   0.0140
 -10.250  -0.6514   0.03564   0.03012  -0.0959   0.9688   0.0142
 -10.000  -0.6379   0.03343   0.02770  -0.0964   0.9626   0.0144
  -9.750  -0.6160   0.03141   0.02548  -0.0980   0.9592   0.0148
  -9.500  -0.6006   0.02979   0.02366  -0.0976   0.9529   0.0151
  -9.250  -0.5781   0.02829   0.02198  -0.0983   0.9486   0.0156
  -9.000  -0.5509   0.02690   0.02038  -0.0997   0.9459   0.0165
  -8.750  -0.5293   0.02564   0.01890  -0.0996   0.9412   0.0172
  -8.500  -0.5065   0.02442   0.01748  -0.0996   0.9364   0.0178
  -8.250  -0.4793   0.02304   0.01595  -0.1005   0.9335   0.0183
  -8.000  -0.4499   0.02174   0.01456  -0.1019   0.9314   0.0191
  -7.750  -0.4287   0.02089   0.01362  -0.1013   0.9257   0.0198
  -7.500  -0.4023   0.02003   0.01266  -0.1017   0.9215   0.0208
  -7.250  -0.3721   0.01917   0.01166  -0.1028   0.9187   0.0223
  -7.000  -0.3404   0.01831   0.01068  -0.1041   0.9165   0.0241
  -6.750  -0.3193   0.01772   0.01006  -0.1032   0.9101   0.0271
  -6.500  -0.2911   0.01704   0.00931  -0.1037   0.9060   0.0318
  -6.250  -0.2598   0.01634   0.00856  -0.1048   0.9032   0.0402
  -6.000  -0.2309   0.01575   0.00797  -0.1054   0.8995   0.0522
  -5.750  -0.2070   0.01533   0.00756  -0.1049   0.8934   0.0651
  -5.500  -0.1763   0.01486   0.00711  -0.1058   0.8898   0.0832
  -5.250  -0.1440   0.01435   0.00668  -0.1071   0.8870   0.1100
  -5.000  -0.1216   0.01401   0.00643  -0.1063   0.8802   0.1342
  -4.750  -0.0921   0.01364   0.00608  -0.1068   0.8758   0.1576
  -4.500  -0.0600   0.01325   0.00573  -0.1079   0.8725   0.1848
  -4.250  -0.0362   0.01300   0.00551  -0.1073   0.8659   0.2095
  -4.000  -0.0074   0.01269   0.00526  -0.1077   0.8610   0.2401
  -3.750   0.0243   0.01235   0.00499  -0.1086   0.8574   0.2766
  -3.500   0.0477   0.01214   0.00486  -0.1079   0.8503   0.3106
  -3.250   0.0768   0.01188   0.00468  -0.1083   0.8453   0.3480
  -3.000   0.1056   0.01166   0.00453  -0.1086   0.8405   0.3851
  -2.750   0.1311   0.01150   0.00444  -0.1081   0.8337   0.4191
  -2.500   0.1611   0.01131   0.00430  -0.1086   0.8290   0.4536
  -2.250   0.1869   0.01120   0.00425  -0.1082   0.8224   0.4852
  -2.000   0.2148   0.01107   0.00417  -0.1082   0.8165   0.5160
  -1.750   0.2433   0.01096   0.00409  -0.1082   0.8110   0.5450
  -1.500   0.2691   0.01088   0.00408  -0.1077   0.8038   0.5727
  -1.250   0.2989   0.01078   0.00399  -0.1080   0.7987   0.6001
  -1.000   0.3235   0.01075   0.00401  -0.1073   0.7909   0.6257
  -0.750   0.3520   0.01067   0.00397  -0.1073   0.7850   0.6508
  -0.500   0.3774   0.01065   0.00400  -0.1067   0.7775   0.6747
  -0.250   0.4049   0.01061   0.00398  -0.1064   0.7710   0.6984
   0.000   0.4304   0.01060   0.00402  -0.1058   0.7635   0.7210
   0.250   0.4572   0.01058   0.00403  -0.1054   0.7565   0.7431
   0.500   0.4824   0.01059   0.00407  -0.1047   0.7488   0.7646
   0.750   0.5085   0.01059   0.00409  -0.1041   0.7415   0.7849
   1.000   0.5327   0.01061   0.00415  -0.1032   0.7334   0.8050
   1.250   0.5588   0.01063   0.00417  -0.1026   0.7259   0.8245
   1.500   0.5817   0.01066   0.00424  -0.1014   0.7171   0.8433
   1.750   0.6068   0.01067   0.00425  -0.1006   0.7093   0.8619
   2.000   0.6297   0.01071   0.00432  -0.0993   0.6998   0.8815
   2.250   0.6538   0.01074   0.00436  -0.0984   0.6906   0.9013
   2.500   0.6801   0.01076   0.00438  -0.0978   0.6813   0.9211
   2.750   0.7079   0.01080   0.00445  -0.0978   0.6707   0.9428
   3.000   0.7420   0.01086   0.00450  -0.0991   0.6600   0.9639
   3.250   0.7788   0.01093   0.00455  -0.1011   0.6486   0.9914
   3.500   0.8048   0.01105   0.00464  -0.1009   0.6369   1.0000
   3.750   0.8285   0.01119   0.00475  -0.1002   0.6242   1.0000
   4.000   0.8524   0.01134   0.00488  -0.0995   0.6113   1.0000
   4.250   0.8762   0.01150   0.00502  -0.0988   0.5980   1.0000
   4.500   0.8997   0.01168   0.00518  -0.0981   0.5840   1.0000
   4.750   0.9227   0.01188   0.00535  -0.0972   0.5687   1.0000
   5.000   0.9452   0.01209   0.00553  -0.0962   0.5524   1.0000
   5.250   0.9670   0.01233   0.00573  -0.0951   0.5352   1.0000
   5.500   0.9881   0.01260   0.00597  -0.0939   0.5172   1.0000
   5.750   1.0085   0.01288   0.00622  -0.0925   0.4973   1.0000
   6.000   1.0276   0.01320   0.00648  -0.0910   0.4762   1.0000
   6.250   1.0459   0.01355   0.00678  -0.0893   0.4537   1.0000
   6.500   1.0624   0.01396   0.00712  -0.0873   0.4298   1.0000
   6.750   1.0778   0.01439   0.00748  -0.0851   0.4045   1.0000
   7.000   1.0907   0.01487   0.00787  -0.0825   0.3784   1.0000
   7.250   1.1022   0.01543   0.00833  -0.0797   0.3505   1.0000
   7.500   1.1129   0.01606   0.00884  -0.0769   0.3217   1.0000
   7.750   1.1234   0.01675   0.00942  -0.0742   0.2936   1.0000
   8.000   1.1338   0.01750   0.01007  -0.0716   0.2670   1.0000
   8.250   1.1450   0.01825   0.01075  -0.0691   0.2422   1.0000
   8.500   1.1555   0.01907   0.01149  -0.0667   0.2180   1.0000
   8.750   1.1646   0.01999   0.01230  -0.0642   0.1931   1.0000
   9.000   1.1731   0.02100   0.01319  -0.0618   0.1681   1.0000
   9.250   1.1810   0.02209   0.01415  -0.0594   0.1424   1.0000
   9.500   1.1887   0.02323   0.01520  -0.0571   0.1192   1.0000
   9.750   1.1968   0.02440   0.01627  -0.0550   0.1006   1.0000
  10.000   1.2062   0.02553   0.01736  -0.0530   0.0870   1.0000
  10.250   1.2156   0.02668   0.01849  -0.0512   0.0751   1.0000
  10.500   1.2248   0.02788   0.01969  -0.0494   0.0641   1.0000
  10.750   1.2330   0.02919   0.02099  -0.0477   0.0537   1.0000
  11.000   1.2411   0.03054   0.02236  -0.0460   0.0454   1.0000
  11.250   1.2483   0.03201   0.02386  -0.0444   0.0383   1.0000
  11.500   1.2537   0.03366   0.02553  -0.0427   0.0325   1.0000
  11.750   1.2605   0.03525   0.02720  -0.0412   0.0282   1.0000
  12.000   1.2641   0.03716   0.02913  -0.0397   0.0250   1.0000
  12.250   1.2696   0.03896   0.03105  -0.0383   0.0227   1.0000
  12.500   1.2739   0.04092   0.03310  -0.0371   0.0209   1.0000
  12.750   1.2745   0.04329   0.03551  -0.0359   0.0193   1.0000
  13.000   1.2793   0.04533   0.03769  -0.0350   0.0181   1.0000
  13.250   1.2824   0.04760   0.04009  -0.0341   0.0171   1.0000
  13.500   1.2843   0.05007   0.04270  -0.0335   0.0163   1.0000
  13.750   1.2853   0.05274   0.04548  -0.0329   0.0158   1.0000
  14.000   1.2840   0.05574   0.04858  -0.0325   0.0152   1.0000
  14.250   1.2810   0.05906   0.05200  -0.0323   0.0148   1.0000
  14.500   1.2793   0.06236   0.05543  -0.0323   0.0145   1.0000
  14.750   1.2788   0.06559   0.05881  -0.0324   0.0141   1.0000
  15.000   1.2777   0.06898   0.06235  -0.0327   0.0139   1.0000
  15.250   1.2763   0.07253   0.06604  -0.0331   0.0135   1.0000
  15.500   1.2746   0.07620   0.06985  -0.0337   0.0132   1.0000
  15.750   1.2726   0.08000   0.07378  -0.0345   0.0128   1.0000
  16.000   1.2703   0.08395   0.07786  -0.0355   0.0125   1.0000
  16.250   1.2676   0.08806   0.08210  -0.0368   0.0122   1.0000
  16.500   1.2642   0.09235   0.08651  -0.0382   0.0119   1.0000
  16.750   1.2599   0.09688   0.09115  -0.0398   0.0116   1.0000
  17.000   1.2550   0.10157   0.09597  -0.0416   0.0113   1.0000
  17.250   1.2502   0.10630   0.10081  -0.0435   0.0112   1.0000
  17.500   1.2449   0.11116   0.10578  -0.0455   0.0109   1.0000
  17.750   1.2405   0.11609   0.11088  -0.0477   0.0108   1.0000
  18.000   1.2355   0.12116   0.11611  -0.0501   0.0107   1.0000
  18.250   1.2296   0.12653   0.12166  -0.0529   0.0106   1.0000
  18.500   1.2233   0.13208   0.12738  -0.0558   0.0105   1.0000
  18.750   1.2164   0.13784   0.13330  -0.0591   0.0104   1.0000
  19.000   1.2081   0.14408   0.13971  -0.0627   0.0103   1.0000
  19.250   1.1994   0.15054   0.14634  -0.0667   0.0103   1.0000
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