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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 500,000
Max Cl/Cd: 107.47 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e67-il-500000-n5.txt
Download as CSV file: xf-e67-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6518   0.05270   0.04991  -0.0810   0.9942   0.0067
 -11.500  -0.6636   0.04219   0.03912  -0.0943   0.9886   0.0067
 -11.250  -0.6664   0.03515   0.03176  -0.1056   0.9815   0.0067
 -11.000  -0.6580   0.03175   0.02811  -0.1094   0.9742   0.0068
 -10.750  -0.6384   0.02906   0.02518  -0.1129   0.9714   0.0069
 -10.500  -0.6267   0.02734   0.02329  -0.1127   0.9642   0.0071
 -10.250  -0.6049   0.02537   0.02109  -0.1144   0.9610   0.0072
 -10.000  -0.5790   0.02374   0.01924  -0.1162   0.9590   0.0074
  -9.750  -0.5613   0.02240   0.01772  -0.1158   0.9533   0.0075
  -9.500  -0.5370   0.02106   0.01620  -0.1166   0.9498   0.0078
  -9.250  -0.5093   0.01978   0.01474  -0.1179   0.9476   0.0079
  -9.000  -0.4793   0.01860   0.01339  -0.1195   0.9459   0.0082
  -8.750  -0.4553   0.01770   0.01235  -0.1195   0.9413   0.0084
  -8.500  -0.4284   0.01691   0.01142  -0.1200   0.9373   0.0087
  -8.250  -0.3979   0.01626   0.01065  -0.1211   0.9347   0.0090
  -8.000  -0.3677   0.01509   0.00935  -0.1226   0.9323   0.0095
  -7.750  -0.3414   0.01436   0.00854  -0.1228   0.9277   0.0099
  -7.500  -0.3135   0.01375   0.00785  -0.1233   0.9232   0.0104
  -7.250  -0.2824   0.01318   0.00719  -0.1243   0.9199   0.0110
  -7.000  -0.2511   0.01265   0.00656  -0.1254   0.9167   0.0116
  -6.750  -0.2251   0.01223   0.00606  -0.1252   0.9108   0.0122
  -6.500  -0.1953   0.01177   0.00551  -0.1259   0.9063   0.0131
  -6.250  -0.1651   0.01133   0.00502  -0.1266   0.9022   0.0148
  -6.000  -0.1385   0.01102   0.00464  -0.1265   0.8961   0.0168
  -5.750  -0.1092   0.01064   0.00425  -0.1270   0.8912   0.0225
  -5.500  -0.0811   0.01032   0.00393  -0.1273   0.8859   0.0311
  -5.250  -0.0536   0.01004   0.00366  -0.1273   0.8800   0.0400
  -5.000  -0.0242   0.00978   0.00338  -0.1278   0.8750   0.0501
  -4.750   0.0025   0.00956   0.00317  -0.1277   0.8687   0.0607
  -4.250   0.0582   0.00906   0.00277  -0.1280   0.8570   0.1009
  -4.000   0.0857   0.00885   0.00259  -0.1281   0.8506   0.1213
  -3.750   0.1140   0.00866   0.00243  -0.1283   0.8448   0.1428
  -3.500   0.1411   0.00850   0.00230  -0.1282   0.8379   0.1634
  -3.000   0.1963   0.00818   0.00206  -0.1283   0.8246   0.2141
  -2.750   0.2243   0.00803   0.00195  -0.1284   0.8179   0.2441
  -2.500   0.2514   0.00789   0.00188  -0.1283   0.8105   0.2740
  -2.250   0.2792   0.00777   0.00179  -0.1284   0.8034   0.3057
  -1.750   0.3339   0.00755   0.00169  -0.1283   0.7882   0.3697
  -1.500   0.3610   0.00745   0.00167  -0.1282   0.7800   0.4027
  -1.250   0.3884   0.00738   0.00164  -0.1282   0.7724   0.4350
  -1.000   0.4156   0.00731   0.00163  -0.1281   0.7638   0.4669
  -0.750   0.4427   0.00726   0.00163  -0.1279   0.7554   0.4978
  -0.500   0.4698   0.00723   0.00163  -0.1278   0.7465   0.5278
  -0.250   0.4966   0.00720   0.00165  -0.1276   0.7368   0.5566
   0.000   0.5234   0.00719   0.00168  -0.1273   0.7273   0.5845
   0.250   0.5499   0.00719   0.00171  -0.1270   0.7172   0.6128
   0.500   0.5764   0.00718   0.00176  -0.1267   0.7066   0.6399
   0.750   0.6027   0.00720   0.00181  -0.1264   0.6960   0.6667
   1.000   0.6286   0.00723   0.00188  -0.1259   0.6849   0.6927
   1.250   0.6542   0.00727   0.00194  -0.1254   0.6734   0.7176
   1.500   0.6797   0.00732   0.00202  -0.1248   0.6608   0.7423
   1.750   0.7047   0.00738   0.00211  -0.1242   0.6477   0.7664
   2.000   0.7292   0.00745   0.00221  -0.1234   0.6337   0.7899
   2.250   0.7533   0.00753   0.00231  -0.1226   0.6192   0.8137
   2.500   0.7765   0.00763   0.00241  -0.1215   0.6041   0.8367
   2.750   0.7989   0.00773   0.00253  -0.1203   0.5882   0.8605
   3.000   0.8203   0.00785   0.00264  -0.1188   0.5719   0.8854
   3.250   0.8404   0.00795   0.00275  -0.1170   0.5544   0.9124
   3.500   0.8613   0.00806   0.00285  -0.1155   0.5360   0.9470
   4.000   0.9135   0.00850   0.00314  -0.1150   0.4927   1.0000
   4.250   0.9362   0.00878   0.00333  -0.1141   0.4699   1.0000
   4.500   0.9587   0.00908   0.00353  -0.1132   0.4451   1.0000
   4.750   0.9807   0.00941   0.00375  -0.1122   0.4198   1.0000
   5.000   1.0021   0.00976   0.00401  -0.1111   0.3932   1.0000
   5.250   1.0228   0.01016   0.00428  -0.1098   0.3642   1.0000
   5.500   1.0431   0.01058   0.00458  -0.1085   0.3354   1.0000
   5.750   1.0624   0.01106   0.00491  -0.1071   0.3040   1.0000
   6.000   1.0813   0.01155   0.00527  -0.1056   0.2731   1.0000
   6.250   1.1000   0.01202   0.00562  -0.1041   0.2468   1.0000
   6.500   1.1179   0.01250   0.00600  -0.1024   0.2217   1.0000
   6.750   1.1344   0.01306   0.00642  -0.1005   0.1936   1.0000
   7.000   1.1504   0.01365   0.00687  -0.0986   0.1660   1.0000
   7.250   1.1651   0.01433   0.00739  -0.0965   0.1358   1.0000
   7.500   1.1807   0.01495   0.00790  -0.0945   0.1139   1.0000
   7.750   1.1976   0.01549   0.00838  -0.0928   0.0987   1.0000
   8.000   1.2140   0.01606   0.00890  -0.0911   0.0839   1.0000
   8.250   1.2297   0.01667   0.00945  -0.0892   0.0703   1.0000
   8.500   1.2452   0.01730   0.01003  -0.0874   0.0587   1.0000
   8.750   1.2606   0.01793   0.01066  -0.0856   0.0495   1.0000
   9.000   1.2754   0.01861   0.01131  -0.0837   0.0413   1.0000
   9.250   1.2894   0.01933   0.01200  -0.0818   0.0337   1.0000
   9.500   1.3035   0.02005   0.01273  -0.0799   0.0274   1.0000
   9.750   1.3168   0.02084   0.01352  -0.0780   0.0221   1.0000
  10.000   1.3290   0.02171   0.01439  -0.0760   0.0180   1.0000
  10.250   1.3426   0.02250   0.01522  -0.0742   0.0157   1.0000
  10.500   1.3542   0.02344   0.01621  -0.0723   0.0136   1.0000
  10.750   1.3666   0.02434   0.01717  -0.0705   0.0124   1.0000
  11.000   1.3788   0.02527   0.01817  -0.0688   0.0114   1.0000
  11.250   1.3896   0.02632   0.01927  -0.0670   0.0105   1.0000
  11.500   1.3984   0.02755   0.02056  -0.0651   0.0095   1.0000
  11.750   1.4093   0.02865   0.02173  -0.0634   0.0089   1.0000
  12.000   1.4191   0.02985   0.02302  -0.0618   0.0084   1.0000
  12.250   1.4283   0.03113   0.02438  -0.0602   0.0078   1.0000
  12.500   1.4360   0.03257   0.02589  -0.0587   0.0072   1.0000
  12.750   1.4416   0.03425   0.02766  -0.0570   0.0068   1.0000
  13.000   1.4464   0.03603   0.02954  -0.0555   0.0065   1.0000
  13.250   1.4529   0.03772   0.03133  -0.0542   0.0063   1.0000
  13.500   1.4580   0.03959   0.03332  -0.0529   0.0060   1.0000
  13.750   1.4628   0.04155   0.03538  -0.0518   0.0057   1.0000
  14.000   1.4660   0.04373   0.03767  -0.0508   0.0055   1.0000
  14.250   1.4689   0.04602   0.04008  -0.0499   0.0053   1.0000
  14.500   1.4709   0.04851   0.04267  -0.0492   0.0051   1.0000
  14.750   1.4721   0.05118   0.04544  -0.0487   0.0049   1.0000
  15.000   1.4716   0.05414   0.04851  -0.0483   0.0048   1.0000
  15.250   1.4696   0.05741   0.05190  -0.0482   0.0047   1.0000
  15.500   1.4665   0.06097   0.05560  -0.0483   0.0046   1.0000
  15.750   1.4588   0.06528   0.06005  -0.0488   0.0044   1.0000
  16.000   1.4512   0.06979   0.06469  -0.0495   0.0043   1.0000
  16.250   1.4467   0.07403   0.06907  -0.0505   0.0042   1.0000
  16.500   1.4417   0.07848   0.07367  -0.0517   0.0042   1.0000
  16.750   1.4354   0.08328   0.07861  -0.0532   0.0041   1.0000
  17.000   1.4277   0.08846   0.08393  -0.0550   0.0041   1.0000
  17.250   1.4183   0.09411   0.08973  -0.0572   0.0040   1.0000
  17.500   1.4089   0.09992   0.09569  -0.0596   0.0040   1.0000
  17.750   1.3986   0.10602   0.10194  -0.0624   0.0039   1.0000
  18.000   1.3879   0.11237   0.10843  -0.0654   0.0039   1.0000
  18.250   1.3770   0.11890   0.11510  -0.0687   0.0039   1.0000
  18.500   1.3656   0.12563   0.12198  -0.0723   0.0038   1.0000
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