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EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 328 AIRFOIL (e328-il)
Reynolds number: 50,000
Max Cl/Cd: 17.63 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e328-il-50000.txt
Download as CSV file: xf-e328-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 328 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3686   0.11103   0.10452  -0.0143   1.0000   0.2346
  -9.250  -0.3682   0.10792   0.10150  -0.0145   1.0000   0.2455
  -9.000  -0.3943   0.10685   0.10059  -0.0162   1.0000   0.2566
  -8.750  -0.3588   0.10174   0.09547  -0.0131   1.0000   0.2793
  -8.500  -0.3539   0.09890   0.09270  -0.0121   1.0000   0.2985
  -8.250  -0.3657   0.09697   0.09091  -0.0113   1.0000   0.3197
  -8.000  -0.3469   0.09367   0.08766  -0.0087   1.0000   0.3499
  -7.750  -0.3383   0.09107   0.08514  -0.0062   1.0000   0.3825
  -7.500  -0.3148   0.08782   0.08193  -0.0030   1.0000   0.4248
  -7.250  -0.3196   0.08667   0.08091   0.0006   1.0000   0.4648
  -7.000  -0.2729   0.08244   0.07666   0.0031   1.0000   0.5204
  -6.750  -0.2624   0.08101   0.07532   0.0071   1.0000   0.5767
  -6.500  -0.2177   0.07703   0.07136   0.0079   1.0000   0.6386
  -5.750  -0.2669   0.06879   0.06364   0.0090   1.0000   0.5730
  -5.500  -0.3326   0.06694   0.06220   0.0119   1.0000   0.5309
  -5.250  -0.3764   0.06664   0.06222   0.0184   1.0000   0.5303
  -5.000  -0.4150   0.06687   0.06267   0.0254   1.0000   0.5316
  -4.750  -0.4566   0.06681   0.06280   0.0318   1.0000   0.5329
  -4.500  -0.5094   0.06125   0.05726   0.0233   0.9862   0.4849
  -4.250  -0.4408   0.04809   0.04083  -0.0119   0.9621   0.1560
  -4.000  -0.3896   0.04435   0.03612  -0.0151   0.9478   0.1256
  -3.750  -0.3414   0.04166   0.03248  -0.0176   0.9332   0.1122
  -3.500  -0.2949   0.03859   0.02911  -0.0206   0.9189   0.1098
  -3.250  -0.2472   0.03659   0.02657  -0.0233   0.9043   0.1120
  -3.000   0.1317   0.02677   0.01935  -0.0653   0.9337   1.0000
  -2.750   0.1963   0.02597   0.01793  -0.0729   0.9127   1.0000
  -2.500   0.2489   0.02540   0.01692  -0.0780   0.8909   1.0000
  -2.250   0.2911   0.02506   0.01621  -0.0810   0.8702   1.0000
  -2.000   0.3192   0.02512   0.01599  -0.0815   0.8489   1.0000
  -1.750   0.3425   0.02532   0.01597  -0.0811   0.8295   1.0000
  -1.500   0.3640   0.02560   0.01604  -0.0802   0.8115   1.0000
  -1.250   0.3851   0.02593   0.01619  -0.0794   0.7952   1.0000
  -1.000   0.4058   0.02633   0.01643  -0.0786   0.7803   1.0000
  -0.750   0.4258   0.02675   0.01672  -0.0776   0.7662   1.0000
  -0.500   0.4458   0.02717   0.01698  -0.0765   0.7536   1.0000
  -0.250   0.4646   0.02767   0.01738  -0.0753   0.7414   1.0000
   0.000   0.4811   0.02837   0.01801  -0.0741   0.7289   1.0000
   0.250   0.4985   0.02903   0.01858  -0.0728   0.7178   1.0000
   0.500   0.5186   0.02948   0.01893  -0.0716   0.7082   1.0000
   0.750   0.5321   0.03048   0.01992  -0.0703   0.6969   1.0000
   1.000   0.5497   0.03118   0.02056  -0.0690   0.6878   1.0000
   1.250   0.5650   0.03205   0.02140  -0.0676   0.6781   1.0000
   1.500   0.5775   0.03318   0.02253  -0.0662   0.6691   1.0000
   1.750   0.5948   0.03391   0.02322  -0.0648   0.6608   1.0000
   2.000   0.6016   0.03544   0.02479  -0.0630   0.6517   1.0000
   2.250   0.6197   0.03616   0.02548  -0.0615   0.6442   1.0000
   2.500   0.6192   0.03817   0.02754  -0.0592   0.6356   1.0000
   2.750   0.6361   0.03898   0.02833  -0.0577   0.6284   1.0000
   3.000   0.6282   0.04140   0.03081  -0.0547   0.6206   1.0000
   3.250   0.6351   0.04282   0.03224  -0.0525   0.6135   1.0000
   3.500   0.6282   0.04504   0.03448  -0.0492   0.6066   1.0000
   3.750   0.6050   0.04797   0.03744  -0.0448   0.6001   1.0000
   4.000   0.6417   0.04797   0.03743  -0.0447   0.5940   1.0000
   4.250   0.5638   0.05308   0.04252  -0.0357   0.5899   1.0000
   4.500   0.5085   0.05621   0.04560  -0.0276   0.5879   1.0000
   4.750   0.4805   0.05863   0.04798  -0.0227   0.5861   1.0000
   5.000   0.4627   0.06089   0.05021  -0.0192   0.5848   1.0000
   5.250   0.4497   0.06316   0.05244  -0.0163   0.5842   1.0000
   5.500   0.4338   0.06586   0.05511  -0.0141   0.5883   1.0000
   5.750   0.4336   0.06842   0.05765  -0.0133   0.5916   1.0000
   6.000   0.3304   0.07579   0.06508  -0.0134   0.7239   1.0000
   6.250   0.3328   0.07677   0.06604  -0.0117   0.7103   1.0000
   6.500   0.3413   0.07841   0.06766  -0.0109   0.6972   1.0000
   6.750   0.3552   0.08056   0.06981  -0.0108   0.6860   1.0000
   7.000   0.3895   0.08415   0.07343  -0.0130   0.6750   1.0000
   7.250   0.3913   0.08515   0.07442  -0.0115   0.6608   1.0000
   7.500   0.3960   0.08675   0.07605  -0.0105   0.6477   1.0000
   7.750   0.4070   0.08901   0.07832  -0.0104   0.6372   1.0000
   8.000   0.4433   0.09304   0.08240  -0.0126   0.6263   1.0000
   8.250   0.4410   0.09393   0.08330  -0.0110   0.6125   1.0000
   8.500   0.4433   0.09568   0.08507  -0.0102   0.6005   1.0000
   8.750   0.4586   0.09855   0.08798  -0.0107   0.5912   1.0000
   9.000   0.4881   0.10215   0.09169  -0.0120   0.5786   1.0000
   9.250   0.4819   0.10313   0.09268  -0.0106   0.5658   1.0000
   9.500   0.4862   0.10540   0.09498  -0.0103   0.5550   1.0000
   9.750   0.5126   0.10927   0.09893  -0.0116   0.5453   1.0000
  10.000   0.5195   0.11123   0.10095  -0.0113   0.5322   1.0000
  10.250   0.5166   0.11310   0.10287  -0.0108   0.5215   1.0000
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