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EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 329 AIRFOIL (e329-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.77 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e329-il-1000000-n5.txt
Download as CSV file: xf-e329-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 329 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  -0.2440   0.08830   0.08573  -0.0621   0.7593   0.0075
  -9.750  -0.2461   0.08475   0.08205  -0.0631   0.7235   0.0076
  -6.750  -0.3656   0.02384   0.01905  -0.0511   0.6002   0.0041
  -6.500  -0.3569   0.01954   0.01414  -0.0479   0.5913   0.0040
  -6.250  -0.3382   0.01737   0.01159  -0.0463   0.5817   0.0040
  -6.000  -0.3159   0.01617   0.01014  -0.0453   0.5718   0.0040
  -5.750  -0.2927   0.01515   0.00892  -0.0444   0.5612   0.0040
  -5.500  -0.2686   0.01437   0.00797  -0.0436   0.5519   0.0040
  -5.250  -0.2445   0.01366   0.00711  -0.0429   0.5428   0.0040
  -5.000  -0.2203   0.01299   0.00630  -0.0421   0.5343   0.0040
  -4.750  -0.1958   0.01255   0.00575  -0.0415   0.5246   0.0040
  -4.500  -0.1712   0.01209   0.00520  -0.0408   0.5163   0.0041
  -4.250  -0.1466   0.01174   0.00476  -0.0401   0.5080   0.0041
  -4.000  -0.1217   0.01139   0.00435  -0.0395   0.5005   0.0041
  -3.750  -0.0970   0.01108   0.00396  -0.0388   0.4930   0.0042
  -3.500  -0.0719   0.01080   0.00363  -0.0383   0.4856   0.0042
  -3.000  -0.0219   0.01027   0.00298  -0.0371   0.4711   0.0046
  -2.750   0.0039   0.01011   0.00277  -0.0366   0.4643   0.0050
  -2.500   0.0300   0.00997   0.00260  -0.0362   0.4583   0.0053
  -2.250   0.0562   0.00985   0.00244  -0.0359   0.4518   0.0058
  -2.000   0.0822   0.00974   0.00230  -0.0355   0.4451   0.0070
  -1.750   0.1088   0.00963   0.00217  -0.0352   0.4394   0.0086
  -1.500   0.1353   0.00955   0.00207  -0.0349   0.4337   0.0112
  -1.250   0.1617   0.00946   0.00199  -0.0346   0.4284   0.0174
  -1.000   0.1883   0.00936   0.00191  -0.0344   0.4232   0.0274
  -0.750   0.2137   0.00919   0.00186  -0.0340   0.4175   0.0645
  -0.500   0.2386   0.00896   0.00180  -0.0335   0.4125   0.1309
  -0.250   0.2389   0.00672   0.00155  -0.0291   0.4095   0.7421
   0.000   0.2642   0.00674   0.00167  -0.0283   0.4048   0.7981
   0.250   0.2910   0.00684   0.00174  -0.0280   0.3995   0.8152
   0.500   0.3186   0.00692   0.00179  -0.0278   0.3953   0.8242
   0.750   0.3459   0.00700   0.00185  -0.0276   0.3908   0.8321
   1.000   0.3729   0.00712   0.00193  -0.0273   0.3863   0.8408
   1.250   0.4008   0.00720   0.00195  -0.0274   0.3818   0.8428
   1.500   0.4290   0.00725   0.00196  -0.0275   0.3779   0.8438
   1.750   0.4570   0.00730   0.00198  -0.0276   0.3740   0.8448
   2.000   0.4847   0.00737   0.00201  -0.0276   0.3695   0.8457
   2.250   0.5126   0.00743   0.00204  -0.0276   0.3658   0.8467
   2.500   0.5406   0.00749   0.00208  -0.0277   0.3621   0.8476
   2.750   0.5683   0.00756   0.00213  -0.0278   0.3583   0.8486
   3.000   0.5957   0.00765   0.00219  -0.0278   0.3536   0.8498
   3.250   0.6234   0.00773   0.00225  -0.0278   0.3503   0.8510
   3.500   0.6511   0.00780   0.00231  -0.0279   0.3468   0.8521
   3.750   0.6786   0.00789   0.00238  -0.0279   0.3425   0.8531
   4.000   0.7058   0.00799   0.00246  -0.0279   0.3383   0.8542
   4.250   0.7333   0.00808   0.00254  -0.0280   0.3347   0.8553
   4.500   0.7608   0.00816   0.00262  -0.0280   0.3308   0.8564
   4.750   0.7879   0.00826   0.00271  -0.0280   0.3267   0.8575
   5.000   0.8146   0.00840   0.00281  -0.0280   0.3216   0.8586
   5.250   0.8420   0.00848   0.00291  -0.0280   0.3179   0.8595
   5.500   0.8689   0.00858   0.00302  -0.0280   0.3134   0.8607
   5.750   0.8952   0.00871   0.00314  -0.0279   0.3085   0.8621
   6.000   0.9217   0.00882   0.00326  -0.0278   0.3039   0.8635
   6.250   0.9481   0.00894   0.00339  -0.0277   0.2987   0.8648
   6.500   0.9738   0.00910   0.00354  -0.0275   0.2929   0.8662
   6.750   1.0001   0.00922   0.00368  -0.0274   0.2873   0.8676
   7.000   1.0256   0.00939   0.00384  -0.0272   0.2804   0.8690
   7.250   1.0510   0.00956   0.00400  -0.0270   0.2736   0.8705
   7.500   1.0761   0.00974   0.00419  -0.0267   0.2662   0.8720
   7.750   1.1010   0.00994   0.00438  -0.0265   0.2586   0.8736
   8.000   1.1251   0.01018   0.00459  -0.0260   0.2498   0.8751
   8.500   1.1725   0.01064   0.00505  -0.0251   0.2320   0.8784
   8.750   1.1949   0.01093   0.00532  -0.0244   0.2220   0.8803
   9.000   1.2173   0.01120   0.00559  -0.0237   0.2120   0.8825
   9.250   1.2383   0.01154   0.00591  -0.0228   0.2007   0.8850
   9.500   1.2584   0.01191   0.00625  -0.0218   0.1885   0.8876
   9.750   1.2772   0.01235   0.00664  -0.0206   0.1749   0.8901
  10.000   1.2955   0.01277   0.00703  -0.0193   0.1633   0.8926
  10.250   1.3115   0.01324   0.00748  -0.0176   0.1502   0.8957
  10.500   1.3251   0.01373   0.00793  -0.0155   0.1378   0.8994
  10.750   1.3359   0.01424   0.00841  -0.0128   0.1261   0.9039
  11.000   1.3470   0.01475   0.00892  -0.0103   0.1166   0.9084
  11.250   1.3576   0.01526   0.00944  -0.0078   0.1081   0.9141
  11.500   1.3663   0.01586   0.01004  -0.0050   0.0992   0.9212
  11.750   1.3741   0.01648   0.01068  -0.0022   0.0920   0.9301
  12.000   1.3819   0.01714   0.01138   0.0003   0.0843   0.9431
  12.250   1.3951   0.01797   0.01225   0.0014   0.0763   0.9634
  12.500   1.4201   0.01904   0.01334  -0.0005   0.0683   0.9948
  12.750   1.4238   0.02008   0.01439   0.0019   0.0629   1.0000
  13.000   1.4287   0.02132   0.01564   0.0037   0.0573   1.0000
  13.250   1.4332   0.02272   0.01706   0.0051   0.0530   1.0000
  13.500   1.4367   0.02432   0.01869   0.0063   0.0482   1.0000
  13.750   1.4365   0.02636   0.02075   0.0073   0.0432   1.0000
  14.000   1.4420   0.02810   0.02255   0.0078   0.0412   1.0000
  14.250   1.4430   0.03032   0.02482   0.0082   0.0378   1.0000
  14.500   1.4421   0.03285   0.02739   0.0084   0.0349   1.0000
  14.750   1.4379   0.03582   0.03040   0.0085   0.0308   1.0000
  15.000   1.4359   0.03864   0.03328   0.0084   0.0290   1.0000
  15.250   1.4339   0.04152   0.03623   0.0082   0.0272   1.0000
  15.500   1.4282   0.04484   0.03960   0.0079   0.0252   1.0000
  15.750   1.4206   0.04843   0.04326   0.0074   0.0231   1.0000
  16.000   1.4198   0.05135   0.04629   0.0069   0.0235   1.0000
  16.250   1.4092   0.05546   0.05044   0.0062   0.0207   1.0000
  16.500   1.4004   0.05944   0.05448   0.0054   0.0190   1.0000
  16.750   1.3938   0.06326   0.05838   0.0045   0.0178   1.0000
  17.000   1.3860   0.06727   0.06246   0.0036   0.0167   1.0000
  17.250   1.3765   0.07159   0.06683   0.0024   0.0154   1.0000
  17.500   1.3720   0.07533   0.07066   0.0014   0.0152   1.0000
  17.750   1.3661   0.07930   0.07471   0.0002   0.0146   1.0000
  18.000   1.3569   0.08377   0.07924  -0.0012   0.0133   1.0000
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