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EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 332 AIRFOIL (e332-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.77 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e332-il-1000000-n5.txt
Download as CSV file: xf-e332-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 332 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3896   0.09179   0.08938  -0.0220   0.7441   0.0057
  -9.250  -0.3946   0.08718   0.08471  -0.0239   0.7213   0.0058
  -7.750  -0.4269   0.06449   0.06169  -0.0325   0.6346   0.0057
  -5.250  -0.3681   0.02277   0.01774  -0.0132   0.5449   0.0037
  -5.000  -0.3544   0.01849   0.01287  -0.0101   0.5367   0.0035
  -4.750  -0.3322   0.01662   0.01067  -0.0087   0.5277   0.0035
  -4.500  -0.3083   0.01517   0.00892  -0.0077   0.5191   0.0034
  -4.250  -0.2836   0.01394   0.00745  -0.0068   0.5093   0.0034
  -4.000  -0.2583   0.01318   0.00652  -0.0061   0.5009   0.0034
  -3.750  -0.2333   0.01241   0.00560  -0.0054   0.4919   0.0034
  -3.500  -0.2079   0.01188   0.00496  -0.0047   0.4845   0.0034
  -3.000  -0.1577   0.01097   0.00385  -0.0033   0.4680   0.0034
  -2.750  -0.1324   0.01065   0.00345  -0.0027   0.4603   0.0034
  -2.500  -0.1068   0.01034   0.00308  -0.0021   0.4537   0.0035
  -2.250  -0.0811   0.01011   0.00279  -0.0016   0.4468   0.0036
  -2.000  -0.0550   0.00990   0.00253  -0.0011   0.4405   0.0036
  -1.750  -0.0291   0.00969   0.00226  -0.0006   0.4335   0.0039
  -1.500  -0.0029   0.00953   0.00206  -0.0002   0.4271   0.0042
  -1.250   0.0237   0.00942   0.00191   0.0002   0.4206   0.0051
  -1.000   0.0503   0.00934   0.00179   0.0005   0.4150   0.0059
  -0.750   0.0770   0.00922   0.00168   0.0008   0.4094   0.0104
  -0.500   0.1033   0.00911   0.00160   0.0012   0.4032   0.0247
  -0.250   0.1292   0.00895   0.00154   0.0016   0.3978   0.0577
   0.000   0.1501   0.00831   0.00147   0.0027   0.3930   0.2456
   0.250   0.1397   0.00614   0.00141   0.0104   0.3898   0.8690
   0.500   0.1652   0.00625   0.00151   0.0112   0.3847   0.8954
   0.750   0.1917   0.00634   0.00158   0.0117   0.3795   0.9069
   1.000   0.2168   0.00648   0.00168   0.0126   0.3744   0.9195
   1.250   0.2430   0.00661   0.00178   0.0132   0.3698   0.9269
   1.500   0.2686   0.00671   0.00185   0.0139   0.3650   0.9333
   1.750   0.2963   0.00678   0.00188   0.0140   0.3599   0.9351
   2.000   0.3242   0.00685   0.00189   0.0140   0.3553   0.9361
   2.250   0.3523   0.00690   0.00191   0.0139   0.3506   0.9370
   2.500   0.3801   0.00696   0.00193   0.0139   0.3458   0.9379
   2.750   0.4078   0.00703   0.00196   0.0139   0.3413   0.9388
   3.000   0.4356   0.00708   0.00200   0.0138   0.3367   0.9399
   3.250   0.4632   0.00715   0.00204   0.0138   0.3321   0.9410
   3.500   0.4905   0.00724   0.00209   0.0139   0.3273   0.9421
   3.750   0.5182   0.00730   0.00213   0.0138   0.3230   0.9430
   4.000   0.5456   0.00737   0.00219   0.0138   0.3183   0.9440
   4.250   0.5727   0.00747   0.00226   0.0138   0.3132   0.9450
   4.500   0.6002   0.00754   0.00232   0.0138   0.3090   0.9459
   4.750   0.6275   0.00763   0.00239   0.0138   0.3039   0.9468
   5.000   0.6547   0.00774   0.00248   0.0138   0.2986   0.9477
   5.250   0.6823   0.00782   0.00258   0.0137   0.2939   0.9487
   5.500   0.7094   0.00793   0.00268   0.0138   0.2882   0.9498
   5.750   0.7363   0.00805   0.00279   0.0138   0.2826   0.9508
   6.000   0.7633   0.00816   0.00291   0.0138   0.2769   0.9519
   6.500   0.8166   0.00842   0.00316   0.0139   0.2644   0.9542
   6.750   0.8427   0.00859   0.00332   0.0140   0.2569   0.9555
   7.000   0.8691   0.00872   0.00346   0.0141   0.2502   0.9568
   7.250   0.8947   0.00891   0.00362   0.0143   0.2414   0.9582
   7.500   0.9202   0.00910   0.00380   0.0145   0.2320   0.9596
   7.750   0.9454   0.00929   0.00399   0.0147   0.2234   0.9610
   8.000   0.9706   0.00955   0.00421   0.0149   0.2110   0.9624
   8.250   0.9958   0.00982   0.00446   0.0151   0.2001   0.9640
   8.500   1.0205   0.01012   0.00473   0.0153   0.1884   0.9658
   8.750   1.0443   0.01046   0.00504   0.0156   0.1744   0.9678
   9.250   1.0901   0.01120   0.00571   0.0166   0.1479   0.9723
   9.500   1.1123   0.01160   0.00608   0.0172   0.1360   0.9748
   9.750   1.1368   0.01209   0.00652   0.0171   0.1208   0.9765
  10.000   1.1605   0.01267   0.00703   0.0171   0.1044   0.9785
  10.250   1.1843   0.01320   0.00753   0.0171   0.0923   0.9808
  10.500   1.2061   0.01384   0.00810   0.0173   0.0787   0.9837
  10.750   1.2283   0.01443   0.00868   0.0175   0.0682   0.9864
  11.000   1.2525   0.01518   0.00937   0.0170   0.0565   0.9880
  11.250   1.2764   0.01588   0.01005   0.0165   0.0476   0.9899
  11.500   1.2967   0.01686   0.01096   0.0163   0.0352   0.9926
  11.750   1.3199   0.01747   0.01161   0.0161   0.0322   0.9957
  12.000   1.3361   0.01828   0.01243   0.0168   0.0271   1.0000
  12.250   1.3282   0.01906   0.01320   0.0221   0.0220   1.0000
  12.500   1.3368   0.01964   0.01385   0.0245   0.0225   1.0000
  12.750   1.3402   0.02063   0.01488   0.0269   0.0196   1.0000
  13.000   1.3366   0.02228   0.01652   0.0292   0.0143   1.0000
  13.250   1.3408   0.02371   0.01802   0.0304   0.0134   1.0000
  13.500   1.3417   0.02562   0.01997   0.0312   0.0111   1.0000
  13.750   1.3403   0.02797   0.02236   0.0316   0.0089   1.0000
  14.000   1.3450   0.02991   0.02439   0.0317   0.0090   1.0000
  14.250   1.3467   0.03224   0.02679   0.0315   0.0084   1.0000
  14.500   1.3458   0.03492   0.02955   0.0313   0.0076   1.0000
  14.750   1.3434   0.03784   0.03256   0.0309   0.0070   1.0000
  15.000   1.3382   0.04111   0.03591   0.0303   0.0061   1.0000
  15.250   1.3356   0.04413   0.03902   0.0298   0.0061   1.0000
  15.500   1.3306   0.04748   0.04245   0.0291   0.0057   1.0000
  15.750   1.3223   0.05123   0.04628   0.0283   0.0051   1.0000
  16.000   1.3192   0.05442   0.04957   0.0275   0.0055   1.0000
  16.250   1.3057   0.05901   0.05422   0.0262   0.0043   1.0000
  16.500   1.2995   0.06281   0.05811   0.0251   0.0044   1.0000
  16.750   1.2908   0.06705   0.06243   0.0238   0.0038   1.0000
  17.000   1.2836   0.07114   0.06661   0.0225   0.0038   1.0000
  17.250   1.2770   0.07523   0.07078   0.0211   0.0037   1.0000
  17.500   1.2705   0.07943   0.07506   0.0196   0.0037   1.0000
  17.750   1.2631   0.08378   0.07950   0.0180   0.0037   1.0000
  18.000   1.2520   0.08873   0.08452   0.0161   0.0031   1.0000
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