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EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 336 AIRFOIL (e336-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.03 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e336-il-1000000.txt
Download as CSV file: xf-e336-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 336 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4921   0.06152   0.05916  -0.0314   0.7628   0.0088
  -8.000  -0.4996   0.05830   0.05574  -0.0290   0.7360   0.0088
  -7.750  -0.5033   0.05505   0.05232  -0.0265   0.7139   0.0090
  -7.500  -0.5036   0.05185   0.04894  -0.0241   0.6953   0.0090
  -7.250  -0.5020   0.04854   0.04544  -0.0215   0.6776   0.0093
  -7.000  -0.4979   0.04523   0.04192  -0.0188   0.6632   0.0095
  -6.750  -0.4917   0.04173   0.03819  -0.0159   0.6504   0.0098
  -6.500  -0.4844   0.03566   0.03161  -0.0107   0.6406   0.0104
  -6.250  -0.4875   0.03072   0.02629  -0.0063   0.6305   0.0107
  -6.000  -0.4722   0.02923   0.02468  -0.0047   0.6173   0.0108
  -5.750  -0.4559   0.02780   0.02308  -0.0030   0.6048   0.0110
  -5.500  -0.4383   0.02641   0.02152  -0.0013   0.5932   0.0112
  -5.250  -0.4199   0.02488   0.01980   0.0004   0.5824   0.0116
  -5.000  -0.4004   0.02312   0.01776   0.0023   0.5722   0.0124
  -4.250  -0.3283   0.01521   0.00857   0.0076   0.5443   0.0081
  -4.000  -0.3010   0.01372   0.00701   0.0079   0.5353   0.0074
  -3.500  -0.2509   0.01206   0.00511   0.0095   0.5174   0.0068
  -3.250  -0.2273   0.01152   0.00448   0.0105   0.5088   0.0067
  -3.000  -0.2031   0.01110   0.00400   0.0114   0.5007   0.0067
  -2.750  -0.1792   0.01075   0.00358   0.0124   0.4926   0.0069
  -2.500  -0.1544   0.01045   0.00324   0.0131   0.4847   0.0071
  -2.250  -0.1298   0.01022   0.00294   0.0139   0.4767   0.0073
  -2.000  -0.1043   0.01001   0.00269   0.0145   0.4687   0.0079
  -1.750  -0.0798   0.00979   0.00241   0.0153   0.4604   0.0097
  -1.500  -0.0560   0.00945   0.00215   0.0163   0.4531   0.0330
  -1.250  -0.0324   0.00921   0.00204   0.0171   0.4451   0.0780
  -1.000  -0.0092   0.00889   0.00194   0.0180   0.4378   0.1458
  -0.750  -0.0038   0.00758   0.00170   0.0221   0.4306   0.4697
  -0.500  -0.0097   0.00621   0.00144   0.0290   0.4249   0.7614
  -0.250   0.0070   0.00642   0.00201   0.0323   0.4157   0.8923
   0.000   0.0332   0.00696   0.00254   0.0335   0.4067   0.9115
   0.250   0.0622   0.00732   0.00283   0.0338   0.3973   0.9186
   0.500   0.0972   0.00780   0.00325   0.0329   0.3887   0.9248
   0.750   0.1223   0.00807   0.00345   0.0338   0.3812   0.9312
   1.000   0.1714   0.00854   0.00385   0.0298   0.3728   0.9335
   1.250   0.2093   0.00874   0.00397   0.0277   0.3665   0.9346
   1.500   0.2395   0.00878   0.00397   0.0272   0.3621   0.9354
   1.750   0.2693   0.00884   0.00397   0.0267   0.3580   0.9362
   2.000   0.2976   0.00890   0.00398   0.0266   0.3535   0.9373
   2.250   0.3250   0.00893   0.00399   0.0266   0.3508   0.9385
   2.500   0.3492   0.00894   0.00398   0.0273   0.3484   0.9403
   2.750   0.3494   0.00886   0.00390   0.0331   0.3466   0.9456
   3.000   0.3776   0.00885   0.00386   0.0330   0.3437   0.9462
   3.250   0.4053   0.00888   0.00385   0.0329   0.3406   0.9468
   3.500   0.4337   0.00895   0.00389   0.0326   0.3375   0.9474
   3.750   0.4627   0.00897   0.00391   0.0322   0.3357   0.9480
   4.000   0.4908   0.00899   0.00394   0.0321   0.3333   0.9486
   4.250   0.5180   0.00903   0.00397   0.0321   0.3309   0.9492
   4.500   0.5450   0.00909   0.00402   0.0321   0.3282   0.9499
   4.750   0.5717   0.00919   0.00410   0.0321   0.3249   0.9508
   5.000   0.5970   0.00928   0.00418   0.0325   0.3220   0.9518
   5.250   0.6227   0.00928   0.00421   0.0328   0.3199   0.9526
   5.500   0.6472   0.00929   0.00425   0.0333   0.3175   0.9537
   5.750   0.6706   0.00932   0.00428   0.0341   0.3147   0.9549
   6.000   0.6925   0.00936   0.00434   0.0351   0.3121   0.9564
   6.250   0.7118   0.00946   0.00441   0.0367   0.3083   0.9582
   6.500   0.7326   0.00949   0.00447   0.0379   0.3057   0.9594
   6.750   0.7582   0.00946   0.00449   0.0382   0.3030   0.9602
   7.000   0.7855   0.00947   0.00453   0.0381   0.2993   0.9608
   7.250   0.8122   0.00953   0.00459   0.0380   0.2949   0.9614
   7.500   0.8386   0.00963   0.00470   0.0380   0.2905   0.9621
   7.750   0.8664   0.00964   0.00476   0.0378   0.2865   0.9626
   8.000   0.8932   0.00969   0.00483   0.0377   0.2810   0.9633
   8.250   0.9197   0.00979   0.00495   0.0377   0.2756   0.9642
   8.500   0.9465   0.00986   0.00504   0.0376   0.2685   0.9651
   8.750   0.9716   0.00998   0.00516   0.0378   0.2609   0.9660
   9.000   0.9956   0.01013   0.00530   0.0382   0.2515   0.9671
   9.250   1.0186   0.01030   0.00547   0.0388   0.2423   0.9684
   9.500   1.0398   0.01050   0.00567   0.0397   0.2336   0.9699
   9.750   1.0595   0.01071   0.00587   0.0409   0.2243   0.9715
  10.000   1.0795   0.01092   0.00608   0.0420   0.2147   0.9730
  10.250   1.1039   0.01121   0.00636   0.0421   0.2038   0.9740
  10.500   1.1279   0.01157   0.00670   0.0421   0.1909   0.9750
  10.750   1.1510   0.01200   0.00709   0.0423   0.1758   0.9761
  11.000   1.1731   0.01248   0.00753   0.0425   0.1609   0.9774
  11.250   1.1940   0.01304   0.00804   0.0429   0.1453   0.9790
  11.500   1.2127   0.01363   0.00858   0.0436   0.1309   0.9811
  11.750   1.2266   0.01418   0.00910   0.0454   0.1188   0.9840
  12.000   1.2460   0.01499   0.00985   0.0455   0.1034   0.9854
  12.250   1.2671   0.01579   0.01061   0.0452   0.0915   0.9865
  12.500   1.2856   0.01671   0.01150   0.0451   0.0794   0.9880
  12.750   1.3029   0.01766   0.01243   0.0450   0.0700   0.9899
  13.000   1.3181   0.01868   0.01348   0.0450   0.0619   0.9923
  13.250   1.3316   0.01992   0.01473   0.0448   0.0550   0.9947
  13.500   1.3449   0.02160   0.01642   0.0435   0.0476   0.9971
  13.750   1.3564   0.02367   0.01851   0.0417   0.0415   0.9993
  14.000   1.3486   0.02529   0.02019   0.0442   0.0393   1.0000
  14.250   1.3348   0.02732   0.02227   0.0471   0.0370   1.0000
  14.500   1.3271   0.03003   0.02502   0.0478   0.0338   1.0000
  14.750   1.3249   0.03250   0.02756   0.0479   0.0320   1.0000
  15.000   1.3150   0.03587   0.03096   0.0478   0.0289   1.0000
  15.250   1.3082   0.03903   0.03419   0.0476   0.0268   1.0000
  15.500   1.3009   0.04230   0.03754   0.0472   0.0253   1.0000
  15.750   1.2876   0.04629   0.04157   0.0467   0.0231   1.0000
  16.000   1.2793   0.04981   0.04518   0.0461   0.0228   1.0000
  16.250   1.2720   0.05331   0.04877   0.0454   0.0225   1.0000
  16.500   1.2619   0.05722   0.05274   0.0445   0.0205   1.0000
  16.750   1.2504   0.06145   0.05703   0.0435   0.0194   1.0000
  17.000   1.2397   0.06565   0.06130   0.0423   0.0182   1.0000
  17.250   1.2311   0.06965   0.06536   0.0411   0.0168   1.0000
  17.500   1.2205   0.07403   0.06980   0.0398   0.0157   1.0000
  17.750   1.2117   0.07824   0.07410   0.0385   0.0155   1.0000
  18.000   1.2025   0.08254   0.07846   0.0371   0.0143   1.0000
  18.250   1.1947   0.08672   0.08271   0.0357   0.0136   1.0000
  18.500   1.1864   0.09097   0.08702   0.0342   0.0130   1.0000
  18.750   1.1770   0.09549   0.09161   0.0325   0.0125   1.0000
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