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EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 338 AIRFOIL (e338-il)
Reynolds number: 500,000
Max Cl/Cd: 88.59 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e338-il-500000-n5.txt
Download as CSV file: xf-e338-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 338 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2163   0.08653   0.08348  -0.0412   0.7083   0.0104
  -9.750  -0.2169   0.08229   0.07920  -0.0426   0.6939   0.0104
  -9.500  -0.2174   0.07818   0.07504  -0.0440   0.6812   0.0104
  -9.250  -0.2187   0.07400   0.07082  -0.0455   0.6699   0.0104
  -9.000  -0.2212   0.06960   0.06640  -0.0473   0.6593   0.0104
  -8.500  -0.2928   0.06951   0.06620  -0.0599   0.6780   0.0104
  -8.000  -0.3159   0.06270   0.05920  -0.0581   0.6543   0.0104
  -7.500  -0.3280   0.05567   0.05196  -0.0550   0.6332   0.0078
  -7.000  -0.3230   0.05033   0.04636  -0.0522   0.6120   0.0073
  -6.750  -0.3171   0.04741   0.04327  -0.0506   0.6025   0.0071
  -6.250  -0.3251   0.03323   0.02824  -0.0418   0.5902   0.0056
  -6.000  -0.3158   0.02946   0.02413  -0.0389   0.5817   0.0056
  -5.750  -0.3096   0.02379   0.01782  -0.0347   0.5746   0.0055
  -5.500  -0.2948   0.01939   0.01263  -0.0316   0.5670   0.0057
  -5.250  -0.2727   0.01781   0.01072  -0.0305   0.5578   0.0058
  -5.000  -0.2487   0.01708   0.00986  -0.0298   0.5489   0.0061
  -4.750  -0.2242   0.01646   0.00908  -0.0291   0.5398   0.0063
  -4.500  -0.1991   0.01575   0.00822  -0.0285   0.5309   0.0065
  -4.250  -0.1741   0.01511   0.00742  -0.0278   0.5221   0.0068
  -4.000  -0.1491   0.01448   0.00666  -0.0271   0.5135   0.0070
  -3.750  -0.1242   0.01400   0.00606  -0.0264   0.5061   0.0074
  -3.500  -0.0993   0.01356   0.00553  -0.0257   0.4988   0.0076
  -3.000  -0.0498   0.01290   0.00475  -0.0244   0.4844   0.0087
  -2.750  -0.0251   0.01264   0.00443  -0.0237   0.4772   0.0093
  -2.500  -0.0002   0.01236   0.00409  -0.0230   0.4708   0.0098
  -2.250   0.0245   0.01209   0.00375  -0.0223   0.4642   0.0103
  -2.000   0.0489   0.01182   0.00344  -0.0215   0.4586   0.0111
  -1.750   0.0743   0.01162   0.00321  -0.0210   0.4527   0.0124
  -1.500   0.0994   0.01145   0.00299  -0.0203   0.4465   0.0146
  -1.250   0.1247   0.01130   0.00282  -0.0197   0.4412   0.0194
  -1.000   0.1500   0.01114   0.00269  -0.0192   0.4356   0.0314
  -0.750   0.1745   0.01095   0.00259  -0.0186   0.4305   0.0635
  -0.500   0.1985   0.01071   0.00252  -0.0179   0.4262   0.1210
  -0.250   0.2002   0.00890   0.00228  -0.0135   0.4226   0.5889
   0.000   0.2062   0.00845   0.00283  -0.0078   0.4186   0.8778
   0.250   0.2291   0.00874   0.00306  -0.0062   0.4136   0.8984
   0.500   0.2536   0.00901   0.00328  -0.0050   0.4095   0.9107
   0.750   0.2767   0.00920   0.00341  -0.0036   0.4054   0.9207
   1.000   0.3069   0.00952   0.00368  -0.0035   0.4010   0.9290
   1.250   0.3285   0.00964   0.00372  -0.0020   0.3970   0.9354
   1.500   0.3566   0.00967   0.00370  -0.0021   0.3931   0.9363
   1.750   0.3844   0.00971   0.00369  -0.0021   0.3890   0.9372
   2.000   0.4114   0.00975   0.00368  -0.0020   0.3854   0.9381
   2.250   0.4381   0.00982   0.00368  -0.0018   0.3816   0.9391
   2.500   0.4651   0.00987   0.00370  -0.0017   0.3782   0.9402
   2.750   0.4916   0.00991   0.00371  -0.0015   0.3745   0.9412
   3.000   0.5177   0.00996   0.00373  -0.0013   0.3710   0.9423
   3.250   0.5431   0.01002   0.00375  -0.0009   0.3675   0.9435
   3.500   0.5684   0.01009   0.00379  -0.0005   0.3642   0.9450
   3.750   0.5939   0.01013   0.00383  -0.0001   0.3610   0.9462
   4.000   0.6190   0.01018   0.00387   0.0003   0.3576   0.9474
   4.250   0.6437   0.01025   0.00392   0.0007   0.3543   0.9486
   4.500   0.6688   0.01035   0.00398   0.0011   0.3508   0.9496
   4.750   0.6959   0.01042   0.00406   0.0011   0.3478   0.9502
   5.000   0.7229   0.01049   0.00415   0.0010   0.3444   0.9510
   5.250   0.7496   0.01058   0.00424   0.0011   0.3406   0.9520
   5.500   0.7756   0.01070   0.00436   0.0012   0.3373   0.9530
   5.750   0.8015   0.01081   0.00447   0.0014   0.3338   0.9540
   6.000   0.8279   0.01089   0.00458   0.0015   0.3302   0.9550
   6.250   0.8536   0.01100   0.00470   0.0016   0.3263   0.9560
   6.500   0.8786   0.01112   0.00483   0.0019   0.3226   0.9572
   6.750   0.9033   0.01125   0.00497   0.0023   0.3189   0.9585
   7.000   0.9286   0.01135   0.00511   0.0025   0.3150   0.9598
   7.250   0.9528   0.01147   0.00526   0.0029   0.3096   0.9611
   7.500   0.9760   0.01162   0.00541   0.0035   0.3034   0.9626
   7.750   1.0019   0.01176   0.00557   0.0036   0.2961   0.9637
   8.000   1.0268   0.01195   0.00576   0.0038   0.2893   0.9650
   8.250   1.0525   0.01210   0.00597   0.0038   0.2839   0.9663
   8.500   1.0771   0.01230   0.00619   0.0040   0.2784   0.9676
   8.750   1.1016   0.01250   0.00642   0.0042   0.2720   0.9691
   9.000   1.1250   0.01273   0.00667   0.0046   0.2645   0.9709
   9.250   1.1481   0.01296   0.00693   0.0051   0.2581   0.9728
   9.500   1.1698   0.01323   0.00722   0.0057   0.2499   0.9749
   9.750   1.1950   0.01354   0.00755   0.0055   0.2405   0.9762
  10.000   1.2191   0.01391   0.00793   0.0055   0.2312   0.9778
  10.500   1.2646   0.01474   0.00879   0.0058   0.2110   0.9822
  10.750   1.2847   0.01520   0.00927   0.0064   0.2018   0.9853
  11.000   1.3067   0.01581   0.00988   0.0063   0.1888   0.9876
  11.250   1.3275   0.01648   0.01054   0.0064   0.1772   0.9910
  11.500   1.3457   0.01724   0.01129   0.0067   0.1647   0.9968
  11.750   1.3525   0.01793   0.01199   0.0092   0.1551   1.0000
  12.000   1.3562   0.01865   0.01273   0.0122   0.1471   1.0000
  12.250   1.3595   0.01964   0.01373   0.0147   0.1380   1.0000
  12.500   1.3604   0.02093   0.01500   0.0170   0.1275   1.0000
  12.750   1.3608   0.02245   0.01652   0.0188   0.1172   1.0000
  13.000   1.3602   0.02423   0.01831   0.0203   0.1075   1.0000
  13.250   1.3596   0.02622   0.02032   0.0213   0.1002   1.0000
  13.500   1.3571   0.02853   0.02267   0.0221   0.0934   1.0000
  13.750   1.3554   0.03093   0.02511   0.0225   0.0870   1.0000
  14.000   1.3483   0.03396   0.02817   0.0228   0.0798   1.0000
  14.250   1.3459   0.03665   0.03094   0.0229   0.0744   1.0000
  14.500   1.3338   0.04039   0.03469   0.0228   0.0657   1.0000
  14.750   1.3229   0.04411   0.03844   0.0225   0.0599   1.0000
  15.000   1.3147   0.04764   0.04203   0.0222   0.0564   1.0000
  15.250   1.3029   0.05163   0.04606   0.0217   0.0527   1.0000
  15.500   1.2969   0.05511   0.04962   0.0211   0.0510   1.0000
  15.750   1.2902   0.05876   0.05335   0.0203   0.0492   1.0000
  16.000   1.2819   0.06271   0.05737   0.0194   0.0473   1.0000
  16.250   1.2747   0.06661   0.06135   0.0184   0.0460   1.0000
  16.500   1.2666   0.07072   0.06552   0.0173   0.0442   1.0000
  16.750   1.2626   0.07435   0.06924   0.0163   0.0427   1.0000
  17.000   1.2587   0.07804   0.07303   0.0151   0.0415   1.0000
  17.250   1.2539   0.08190   0.07697   0.0139   0.0401   1.0000
  17.500   1.2473   0.08609   0.08122   0.0125   0.0386   1.0000
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