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EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 336 AIRFOIL (e336-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.74 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e336-il-1000000-n5.txt
Download as CSV file: xf-e336-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4168   0.09207   0.08932  -0.0225   0.6518   0.0066
  -8.500  -0.4996   0.06351   0.06054  -0.0316   0.5982   0.0063
  -7.000  -0.5750   0.02597   0.02111  -0.0037   0.5626   0.0037
  -6.750  -0.5657   0.02233   0.01696  -0.0003   0.5533   0.0036
  -6.500  -0.5496   0.01975   0.01395   0.0020   0.5426   0.0036
  -6.250  -0.5284   0.01821   0.01214   0.0033   0.5331   0.0035
  -6.000  -0.5056   0.01688   0.01055   0.0044   0.5244   0.0035
  -5.750  -0.4814   0.01597   0.00947   0.0052   0.5148   0.0035
  -5.500  -0.4570   0.01508   0.00840   0.0060   0.5063   0.0035
  -5.250  -0.4323   0.01435   0.00753   0.0067   0.4979   0.0035
  -5.000  -0.4076   0.01371   0.00676   0.0074   0.4903   0.0035
  -4.750  -0.3830   0.01315   0.00610   0.0081   0.4825   0.0035
  -4.500  -0.3586   0.01266   0.00552   0.0089   0.4753   0.0036
  -4.250  -0.3338   0.01228   0.00506   0.0096   0.4678   0.0036
  -4.000  -0.3094   0.01189   0.00459   0.0104   0.4607   0.0036
  -3.750  -0.2847   0.01156   0.00420   0.0111   0.4539   0.0036
  -3.500  -0.2600   0.01127   0.00385   0.0118   0.4470   0.0037
  -3.250  -0.2349   0.01101   0.00354   0.0124   0.4409   0.0037
  -3.000  -0.2098   0.01078   0.00327   0.0131   0.4341   0.0038
  -2.750  -0.1852   0.01052   0.00294   0.0138   0.4281   0.0040
  -2.500  -0.1597   0.01033   0.00273   0.0144   0.4217   0.0044
  -2.250  -0.1341   0.01020   0.00255   0.0149   0.4150   0.0047
  -2.000  -0.1082   0.01008   0.00239   0.0154   0.4082   0.0056
  -1.750  -0.0825   0.00996   0.00225   0.0159   0.3997   0.0069
  -1.500  -0.0567   0.00986   0.00213   0.0164   0.3926   0.0098
  -1.250  -0.0311   0.00975   0.00202   0.0169   0.3840   0.0179
  -1.000  -0.0058   0.00961   0.00193   0.0174   0.3763   0.0354
  -0.750   0.0184   0.00943   0.00185   0.0181   0.3664   0.0766
  -0.500   0.0412   0.00915   0.00178   0.0190   0.3569   0.1517
  -0.250   0.0251   0.00691   0.00140   0.0273   0.3523   0.6870
   0.000   0.0342   0.00652   0.00168   0.0319   0.3471   0.8743
   0.250   0.0603   0.00667   0.00179   0.0325   0.3420   0.8881
   0.500   0.0857   0.00685   0.00191   0.0332   0.3383   0.8986
   0.750   0.1139   0.00703   0.00207   0.0334   0.3356   0.9049
   1.000   0.1410   0.00720   0.00221   0.0338   0.3328   0.9108
   1.250   0.1666   0.00732   0.00229   0.0344   0.3300   0.9155
   1.500   0.1946   0.00737   0.00230   0.0344   0.3277   0.9166
   1.750   0.2225   0.00742   0.00231   0.0344   0.3256   0.9173
   2.000   0.2503   0.00748   0.00233   0.0343   0.3230   0.9180
   2.250   0.2784   0.00753   0.00235   0.0343   0.3214   0.9187
   2.500   0.3064   0.00757   0.00237   0.0342   0.3198   0.9194
   2.750   0.3343   0.00761   0.00240   0.0341   0.3183   0.9200
   3.000   0.3621   0.00766   0.00243   0.0341   0.3166   0.9206
   3.250   0.3897   0.00771   0.00247   0.0340   0.3145   0.9213
   3.500   0.4172   0.00778   0.00252   0.0340   0.3123   0.9221
   3.750   0.4446   0.00785   0.00258   0.0340   0.3103   0.9229
   4.000   0.4717   0.00795   0.00265   0.0340   0.3076   0.9237
   4.250   0.4992   0.00800   0.00270   0.0340   0.3060   0.9244
   4.500   0.5270   0.00804   0.00276   0.0339   0.3045   0.9250
   4.750   0.5547   0.00809   0.00281   0.0338   0.3024   0.9257
   5.000   0.5822   0.00815   0.00287   0.0337   0.2999   0.9264
   5.250   0.6094   0.00822   0.00294   0.0337   0.2968   0.9270
   5.500   0.6365   0.00831   0.00303   0.0337   0.2938   0.9277
   5.750   0.6635   0.00840   0.00312   0.0336   0.2909   0.9284
   6.000   0.6911   0.00846   0.00320   0.0335   0.2886   0.9290
   6.250   0.7184   0.00852   0.00328   0.0334   0.2846   0.9297
   6.500   0.7454   0.00861   0.00337   0.0334   0.2800   0.9303
   6.750   0.7724   0.00870   0.00346   0.0334   0.2755   0.9309
   7.000   0.7994   0.00878   0.00356   0.0333   0.2686   0.9316
   7.250   0.8258   0.00891   0.00367   0.0334   0.2600   0.9323
   7.500   0.8516   0.00907   0.00381   0.0335   0.2507   0.9330
   7.750   0.8774   0.00923   0.00397   0.0336   0.2432   0.9337
   8.000   0.9023   0.00944   0.00416   0.0338   0.2347   0.9345
   8.250   0.9275   0.00962   0.00435   0.0340   0.2271   0.9353
   8.500   0.9520   0.00985   0.00457   0.0343   0.2190   0.9361
   8.750   0.9761   0.01009   0.00480   0.0347   0.2096   0.9370
   9.000   0.9999   0.01035   0.00505   0.0351   0.1990   0.9380
   9.250   1.0227   0.01066   0.00533   0.0356   0.1871   0.9391
   9.500   1.0448   0.01100   0.00564   0.0362   0.1750   0.9402
   9.750   1.0659   0.01138   0.00598   0.0370   0.1620   0.9416
  10.000   1.0858   0.01181   0.00636   0.0379   0.1483   0.9430
  10.250   1.1056   0.01223   0.00675   0.0388   0.1368   0.9443
  10.750   1.1412   0.01319   0.00765   0.0413   0.1122   0.9473
  11.000   1.1565   0.01373   0.00815   0.0429   0.1002   0.9492
  11.250   1.1701   0.01429   0.00869   0.0447   0.0890   0.9515
  11.500   1.1822   0.01479   0.00919   0.0469   0.0810   0.9541
  11.750   1.1916   0.01529   0.00970   0.0495   0.0743   0.9575
  12.000   1.1974   0.01598   0.01038   0.0525   0.0657   0.9614
  12.250   1.2069   0.01668   0.01110   0.0545   0.0599   0.9658
  12.500   1.2160   0.01751   0.01195   0.0562   0.0532   0.9713
  12.750   1.2294   0.01861   0.01307   0.0564   0.0467   0.9761
  13.000   1.2444   0.01999   0.01447   0.0555   0.0407   0.9806
  13.250   1.2603   0.02145   0.01597   0.0542   0.0361   0.9846
  13.500   1.2756   0.02332   0.01789   0.0521   0.0315   0.9873
  13.750   1.2884   0.02553   0.02014   0.0498   0.0278   0.9901
  14.000   1.2998   0.02778   0.02245   0.0478   0.0250   0.9940
  14.250   1.2997   0.03040   0.02512   0.0474   0.0228   1.0000
  14.500   1.2960   0.03301   0.02779   0.0476   0.0208   1.0000
  14.750   1.2924   0.03574   0.03059   0.0476   0.0198   1.0000
  15.000   1.2842   0.03904   0.03395   0.0473   0.0178   1.0000
  15.250   1.2760   0.04240   0.03737   0.0470   0.0161   1.0000
  15.500   1.2671   0.04592   0.04097   0.0465   0.0151   1.0000
  15.750   1.2565   0.04968   0.04479   0.0459   0.0133   1.0000
  16.000   1.2531   0.05273   0.04793   0.0453   0.0140   1.0000
  16.250   1.2484   0.05600   0.05130   0.0446   0.0144   1.0000
  16.750   1.2267   0.06434   0.05976   0.0425   0.0117   1.0000
  17.000   1.2180   0.06834   0.06383   0.0414   0.0108   1.0000
  17.250   1.2051   0.07300   0.06853   0.0400   0.0093   1.0000
  17.500   1.1979   0.07698   0.07258   0.0387   0.0087   1.0000
  17.750   1.1934   0.08065   0.07634   0.0376   0.0092   1.0000
  18.000   1.1843   0.08498   0.08073   0.0361   0.0080   1.0000
  18.250   1.1765   0.08918   0.08499   0.0347   0.0075   1.0000
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