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EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 332 AIRFOIL (e332-il)
Reynolds number: 500,000
Max Cl/Cd: 95.61 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e332-il-500000.txt
Download as CSV file: xf-e332-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4068   0.08830   0.08619  -0.0158   1.0000   0.0138
  -8.500  -0.4094   0.08383   0.08176  -0.0189   1.0000   0.0142
  -8.250  -0.4126   0.07982   0.07778  -0.0218   1.0000   0.0140
  -8.000  -0.4227   0.07538   0.07335  -0.0249   1.0000   0.0142
  -7.750  -0.4327   0.07202   0.06999  -0.0248   1.0000   0.0142
  -7.500  -0.4385   0.06758   0.06547  -0.0256   1.0000   0.0145
  -7.250  -0.4385   0.06405   0.06188  -0.0251   1.0000   0.0146
  -7.000  -0.4322   0.05988   0.05759  -0.0253   0.9925   0.0148
  -6.750  -0.3919   0.05350   0.05088  -0.0328   0.9152   0.0149
  -6.500  -0.3904   0.04821   0.04521  -0.0322   0.8475   0.0152
  -6.250  -0.3834   0.04597   0.04272  -0.0304   0.8070   0.0155
  -6.000  -0.3732   0.04396   0.04051  -0.0289   0.7773   0.0158
  -5.750  -0.3610   0.04174   0.03807  -0.0273   0.7530   0.0162
  -5.500  -0.3474   0.03944   0.03555  -0.0257   0.7322   0.0167
  -5.250  -0.3322   0.03702   0.03288  -0.0239   0.7132   0.0175
  -5.000  -0.3095   0.03494   0.03034  -0.0212   0.6968   0.0196
  -4.750  -0.2921   0.03333   0.02833  -0.0190   0.6809   0.0198
  -4.500  -0.2825   0.02866   0.02347  -0.0172   0.6674   0.0207
  -4.250  -0.2631   0.02716   0.02184  -0.0162   0.6527   0.0215
  -4.000  -0.2421   0.02576   0.02023  -0.0150   0.6389   0.0226
  -3.750  -0.2155   0.02590   0.01998  -0.0132   0.6254   0.0260
  -3.500  -0.1988   0.02220   0.01595  -0.0115   0.6139   0.0276
  -3.250  -0.1754   0.02086   0.01452  -0.0107   0.6013   0.0291
  -3.000  -0.1447   0.01622   0.00913  -0.0080   0.5919   0.0139
  -2.750  -0.1165   0.01452   0.00703  -0.0069   0.5810   0.0113
  -2.500  -0.0902   0.01365   0.00605  -0.0062   0.5698   0.0110
  -2.250  -0.0654   0.01282   0.00512  -0.0054   0.5591   0.0110
  -2.000  -0.0411   0.01225   0.00446  -0.0044   0.5491   0.0111
  -1.750  -0.0185   0.01153   0.00368  -0.0032   0.5391   0.0118
  -1.500   0.0062   0.01120   0.00329  -0.0024   0.5299   0.0131
  -1.000   0.0546   0.01043   0.00256  -0.0005   0.5121   0.0513
  -0.750   0.0657   0.00898   0.00233   0.0022   0.5050   0.4086
  -0.500   0.0635   0.00763   0.00274   0.0094   0.4984   0.8951
  -0.250   0.1099   0.00872   0.00373   0.0076   0.4892   0.9380
   0.000   0.1797   0.00937   0.00418  -0.0004   0.4784   0.9492
   0.250   0.2545   0.00998   0.00463  -0.0096   0.4674   0.9624
   0.500   0.3165   0.01014   0.00462  -0.0165   0.4584   0.9690
   0.750   0.3449   0.01020   0.00461  -0.0166   0.4510   0.9731
   1.000   0.3742   0.01022   0.00453  -0.0171   0.4446   0.9755
   1.250   0.4084   0.01014   0.00441  -0.0185   0.4374   0.9768
   1.500   0.4405   0.01014   0.00432  -0.0196   0.4309   0.9784
   1.750   0.4718   0.01011   0.00426  -0.0204   0.4245   0.9801
   2.000   0.5012   0.01013   0.00422  -0.0209   0.4184   0.9821
   2.250   0.5288   0.01017   0.00422  -0.0210   0.4127   0.9841
   2.500   0.5548   0.01023   0.00426  -0.0208   0.4069   0.9862
   2.750   0.5864   0.01023   0.00419  -0.0218   0.4012   0.9872
   3.000   0.6178   0.01018   0.00415  -0.0227   0.3955   0.9883
   3.250   0.6484   0.01019   0.00412  -0.0235   0.3900   0.9896
   3.500   0.6773   0.01025   0.00415  -0.0239   0.3847   0.9909
   3.750   0.7066   0.01025   0.00417  -0.0244   0.3791   0.9923
   4.000   0.7348   0.01032   0.00420  -0.0247   0.3739   0.9936
   4.250   0.7622   0.01039   0.00428  -0.0248   0.3687   0.9948
   4.500   0.7922   0.01040   0.00432  -0.0255   0.3631   0.9958
   4.750   0.8213   0.01048   0.00435  -0.0260   0.3578   0.9968
   5.000   0.8498   0.01051   0.00443  -0.0264   0.3524   0.9976
   5.250   0.8788   0.01055   0.00449  -0.0269   0.3467   0.9987
   5.500   0.9078   0.01067   0.00458  -0.0274   0.3411   0.9997
   5.750   0.9339   0.01071   0.00469  -0.0273   0.3354   1.0000
   6.000   0.9571   0.01084   0.00483  -0.0266   0.3299   1.0000
   6.250   0.9805   0.01097   0.00499  -0.0259   0.3243   1.0000
   6.500   1.0039   0.01107   0.00513  -0.0252   0.3183   1.0000
   6.750   1.0265   0.01124   0.00531  -0.0245   0.3124   1.0000
   7.000   1.0499   0.01133   0.00547  -0.0238   0.3059   1.0000
   7.500   1.0950   0.01163   0.00583  -0.0222   0.2922   1.0000
   7.750   1.1166   0.01184   0.00605  -0.0213   0.2851   1.0000
   8.000   1.1391   0.01196   0.00624  -0.0205   0.2766   1.0000
   8.250   1.1603   0.01218   0.00648  -0.0195   0.2690   1.0000
   8.500   1.1817   0.01236   0.00671  -0.0185   0.2601   1.0000
   8.750   1.2025   0.01258   0.00698  -0.0175   0.2500   1.0000
   9.000   1.2223   0.01286   0.00727  -0.0163   0.2401   1.0000
   9.250   1.2411   0.01317   0.00759  -0.0150   0.2283   1.0000
   9.750   1.2757   0.01394   0.00835  -0.0119   0.2014   1.0000
  10.000   1.2909   0.01440   0.00882  -0.0100   0.1860   1.0000
  10.250   1.3043   0.01493   0.00932  -0.0078   0.1705   1.0000
  10.500   1.3156   0.01551   0.00987  -0.0053   0.1557   1.0000
  10.750   1.3243   0.01614   0.01047  -0.0024   0.1413   1.0000
  11.000   1.3301   0.01679   0.01109   0.0010   0.1278   1.0000
  11.250   1.3326   0.01746   0.01173   0.0049   0.1153   1.0000
  11.500   1.3326   0.01810   0.01236   0.0093   0.1054   1.0000
  11.750   1.3303   0.01879   0.01304   0.0140   0.0963   1.0000
  12.000   1.3242   0.01951   0.01376   0.0192   0.0884   1.0000
  12.250   1.3238   0.02032   0.01460   0.0230   0.0813   1.0000
  12.500   1.3226   0.02147   0.01575   0.0261   0.0736   1.0000
  12.750   1.3223   0.02285   0.01716   0.0284   0.0672   1.0000
  13.000   1.3225   0.02447   0.01883   0.0300   0.0611   1.0000
  13.250   1.3192   0.02665   0.02103   0.0311   0.0556   1.0000
  13.500   1.3196   0.02879   0.02325   0.0316   0.0510   1.0000
  13.750   1.3155   0.03152   0.02603   0.0317   0.0470   1.0000
  14.000   1.3115   0.03443   0.02902   0.0316   0.0431   1.0000
  14.250   1.3071   0.03749   0.03215   0.0313   0.0399   1.0000
  14.500   1.2961   0.04137   0.03608   0.0307   0.0370   1.0000
  14.750   1.2899   0.04478   0.03960   0.0301   0.0345   1.0000
  15.000   1.2820   0.04846   0.04334   0.0293   0.0319   1.0000
  15.250   1.2708   0.05258   0.04753   0.0284   0.0305   1.0000
  15.500   1.2548   0.05737   0.05238   0.0272   0.0283   1.0000
  15.750   1.2493   0.06103   0.05618   0.0262   0.0270   1.0000
  16.000   1.2406   0.06523   0.06046   0.0249   0.0254   1.0000
  16.250   1.2299   0.06979   0.06507   0.0234   0.0238   1.0000
  16.500   1.2151   0.07505   0.07040   0.0216   0.0228   1.0000
  16.750   1.2067   0.07955   0.07499   0.0200   0.0213   1.0000
  17.000   1.1988   0.08403   0.07957   0.0183   0.0205   1.0000
  17.250   1.1933   0.08822   0.08385   0.0167   0.0195   1.0000
  17.500   1.1837   0.09317   0.08886   0.0147   0.0185   1.0000
  17.750   1.1722   0.09846   0.09423   0.0126   0.0179   1.0000
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