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EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 428 AIRFOIL (e428-il)
Reynolds number: 50,000
Max Cl/Cd: 22.09 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e428-il-50000.txt
Download as CSV file: xf-e428-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 428 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5210   0.10005   0.09223   0.0243   1.0000   0.4121
  -8.250  -0.4946   0.09577   0.08786   0.0246   1.0000   0.4258
  -8.000  -0.6198   0.07761   0.07009   0.0014   1.0000   0.2773
  -7.750  -0.6201   0.07189   0.06435  -0.0013   1.0000   0.2725
  -7.500  -0.6341   0.06471   0.05715  -0.0059   1.0000   0.2693
  -7.250  -0.6493   0.05716   0.04946  -0.0107   1.0000   0.2690
  -7.000  -0.6562   0.05050   0.04250  -0.0141   1.0000   0.2723
  -6.750  -0.6514   0.04561   0.03728  -0.0156   1.0000   0.2786
  -6.500  -0.6336   0.04349   0.03505  -0.0150   1.0000   0.2889
  -6.250  -0.6174   0.04092   0.03231  -0.0147   1.0000   0.2988
  -6.000  -0.6035   0.03781   0.02878  -0.0152   1.0000   0.3107
  -5.750  -0.5813   0.03664   0.02765  -0.0139   1.0000   0.3227
  -5.500  -0.5609   0.03517   0.02613  -0.0130   1.0000   0.3356
  -5.250  -0.5410   0.03350   0.02431  -0.0123   1.0000   0.3490
  -5.000  -0.5209   0.03171   0.02230  -0.0120   1.0000   0.3624
  -4.750  -0.4988   0.03047   0.02101  -0.0111   1.0000   0.3748
  -4.500  -0.4769   0.02926   0.01980  -0.0102   1.0000   0.3870
  -4.250  -0.4550   0.02790   0.01830  -0.0096   1.0000   0.3995
  -4.000  -0.4329   0.02670   0.01698  -0.0090   1.0000   0.4134
  -3.750  -0.4107   0.02572   0.01594  -0.0082   1.0000   0.4280
  -3.500  -0.3886   0.02486   0.01514  -0.0070   1.0000   0.4416
  -3.250  -0.3667   0.02403   0.01435  -0.0060   1.0000   0.4567
  -3.000  -0.3451   0.02327   0.01362  -0.0050   1.0000   0.4729
  -2.750  -0.3240   0.02259   0.01298  -0.0038   1.0000   0.4904
  -2.500  -0.3033   0.02196   0.01241  -0.0027   1.0000   0.5093
  -2.250  -0.2828   0.02138   0.01187  -0.0016   1.0000   0.5304
  -2.000  -0.2640   0.02089   0.01154  -0.0001   1.0000   0.5518
  -1.750  -0.2464   0.02047   0.01125   0.0016   1.0000   0.5755
  -1.500  -0.2294   0.02010   0.01101   0.0033   1.0000   0.6039
  -1.250  -0.2131   0.01979   0.01086   0.0051   1.0000   0.6370
  -1.000  -0.1988   0.01953   0.01081   0.0074   1.0000   0.6761
  -0.750  -0.1867   0.01928   0.01083   0.0103   1.0000   0.7268
  -0.500  -0.1781   0.01900   0.01087   0.0141   1.0000   0.7922
  -0.250  -0.1553   0.01873   0.01098   0.0161   1.0000   0.8964
   0.000  -0.0713   0.01866   0.01077   0.0021   1.0000   1.0000
   0.250  -0.0368   0.01910   0.01098  -0.0029   0.9887   1.0000
   0.500   0.0633   0.01978   0.01155  -0.0172   0.9528   1.0000
   0.750   0.1596   0.01981   0.01161  -0.0292   0.9156   1.0000
   1.000   0.2449   0.01938   0.01123  -0.0377   0.8757   1.0000
   1.250   0.2912   0.01915   0.01094  -0.0390   0.8319   1.0000
   1.500   0.3190   0.01911   0.01077  -0.0368   0.7875   1.0000
   1.750   0.3375   0.01926   0.01074  -0.0332   0.7398   1.0000
   2.000   0.3555   0.01948   0.01074  -0.0295   0.6900   1.0000
   2.250   0.3743   0.01980   0.01078  -0.0262   0.6386   1.0000
   2.500   0.3946   0.02024   0.01093  -0.0235   0.5900   1.0000
   2.750   0.4165   0.02078   0.01117  -0.0214   0.5484   1.0000
   3.000   0.4394   0.02140   0.01155  -0.0199   0.5139   1.0000
   3.250   0.4631   0.02213   0.01215  -0.0187   0.4852   1.0000
   3.500   0.4875   0.02286   0.01268  -0.0177   0.4621   1.0000
   3.750   0.5121   0.02367   0.01335  -0.0168   0.4420   1.0000
   4.000   0.5369   0.02459   0.01423  -0.0161   0.4247   1.0000
   4.250   0.5619   0.02551   0.01507  -0.0154   0.4094   1.0000
   4.500   0.5862   0.02654   0.01616  -0.0148   0.3945   1.0000
   4.750   0.6102   0.02777   0.01753  -0.0144   0.3818   1.0000
   5.000   0.6341   0.02904   0.01886  -0.0138   0.3704   1.0000
   5.250   0.6594   0.03009   0.01980  -0.0131   0.3597   1.0000
   5.500   0.6807   0.03178   0.02181  -0.0128   0.3489   1.0000
   5.750   0.7033   0.03333   0.02346  -0.0122   0.3394   1.0000
   6.000   0.7262   0.03476   0.02495  -0.0116   0.3292   1.0000
   6.250   0.7442   0.03705   0.02755  -0.0113   0.3201   1.0000
   6.500   0.7700   0.03815   0.02850  -0.0103   0.3105   1.0000
   6.750   0.7809   0.04127   0.03214  -0.0102   0.3011   1.0000
   7.000   0.8020   0.04301   0.03390  -0.0094   0.2917   1.0000
   7.250   0.8118   0.04627   0.03751  -0.0092   0.2829   1.0000
   7.500   0.8279   0.04880   0.04014  -0.0086   0.2750   1.0000
   7.750   0.8212   0.05433   0.04611  -0.0096   0.2697   1.0000
   8.000   0.8548   0.05471   0.04631  -0.0077   0.2607   1.0000
   8.250   0.8312   0.06233   0.05435  -0.0099   0.2592   1.0000
   8.500   0.8070   0.07018   0.06236  -0.0128   0.2596   1.0000
   8.750   0.7928   0.07724   0.06950  -0.0156   0.2613   1.0000
   9.000   0.6054   0.10834   0.10022  -0.0486   0.4276   1.0000
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