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EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 344 AIRFOIL (e344-il)
Reynolds number: 50,000
Max Cl/Cd: 24.46 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e344-il-50000-n5.txt
Download as CSV file: xf-e344-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 344 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2671   0.10754   0.10143  -0.0361   1.0000   0.1120
  -9.000  -0.2936   0.10599   0.10008  -0.0399   1.0000   0.1145
  -8.750  -0.3177   0.10398   0.09826  -0.0421   1.0000   0.1149
  -8.500  -0.2794   0.09865   0.09299  -0.0377   1.0000   0.1182
  -8.250  -0.2783   0.09599   0.09048  -0.0368   1.0000   0.1204
  -8.000  -0.2856   0.09376   0.08845  -0.0361   0.9994   0.1233
  -7.750  -0.3064   0.09009   0.08475  -0.0474   0.9370   0.1312
  -7.500  -0.2654   0.08407   0.07877  -0.0494   0.9197   0.1365
  -7.250  -0.2689   0.07341   0.06740  -0.0606   0.8904   0.0583
  -7.000  -0.2424   0.06889   0.06280  -0.0636   0.8698   0.0569
  -6.750  -0.2267   0.06496   0.05866  -0.0653   0.8472   0.0552
  -6.250  -0.2142   0.05749   0.05017  -0.0647   0.8080   0.0488
  -6.000  -0.1997   0.05461   0.04709  -0.0640   0.7904   0.0483
  -5.750  -0.1867   0.05197   0.04420  -0.0629   0.7739   0.0476
  -5.500  -0.1734   0.04952   0.04144  -0.0614   0.7587   0.0468
  -5.250  -0.1594   0.04708   0.03865  -0.0598   0.7450   0.0461
  -5.000  -0.1440   0.04473   0.03588  -0.0580   0.7323   0.0454
  -4.750  -0.1282   0.04260   0.03336  -0.0562   0.7190   0.0450
  -4.500  -0.1102   0.04056   0.03091  -0.0544   0.7069   0.0448
  -4.250  -0.0892   0.03862   0.02851  -0.0530   0.6964   0.0447
  -4.000  -0.0682   0.03694   0.02645  -0.0515   0.6848   0.0455
  -3.750  -0.0445   0.03541   0.02448  -0.0502   0.6743   0.0472
  -3.500  -0.0183   0.03395   0.02254  -0.0492   0.6646   0.0492
  -3.250   0.0076   0.03266   0.02115  -0.0488   0.6540   0.0513
  -3.000   0.0398   0.03131   0.01951  -0.0488   0.6458   0.0535
  -2.750   0.0723   0.03033   0.01828  -0.0490   0.6353   0.0574
  -2.500   0.1107   0.02929   0.01709  -0.0503   0.6271   0.0638
  -2.250   0.1428   0.02852   0.01616  -0.0505   0.6177   0.0716
  -2.000   0.1713   0.02783   0.01528  -0.0501   0.6108   0.0832
  -1.750   0.3875   0.02436   0.01421  -0.0791   0.5958   1.0000
  -1.500   0.4083   0.02451   0.01409  -0.0782   0.5879   1.0000
  -1.250   0.4296   0.02464   0.01393  -0.0773   0.5811   1.0000
  -1.000   0.4511   0.02480   0.01383  -0.0765   0.5750   1.0000
  -0.750   0.4714   0.02505   0.01391  -0.0756   0.5678   1.0000
  -0.500   0.4931   0.02521   0.01382  -0.0746   0.5623   1.0000
  -0.250   0.5132   0.02551   0.01397  -0.0737   0.5559   1.0000
   0.000   0.5334   0.02580   0.01413  -0.0727   0.5499   1.0000
   0.250   0.5551   0.02602   0.01415  -0.0718   0.5452   1.0000
   0.500   0.5744   0.02643   0.01446  -0.0707   0.5395   1.0000
   0.750   0.5935   0.02683   0.01478  -0.0695   0.5337   1.0000
   1.000   0.6146   0.02711   0.01491  -0.0685   0.5292   1.0000
   1.250   0.6341   0.02753   0.01523  -0.0674   0.5246   1.0000
   1.500   0.6509   0.02813   0.01583  -0.0660   0.5189   1.0000
   1.750   0.6702   0.02857   0.01619  -0.0648   0.5145   1.0000
   2.000   0.6917   0.02888   0.01636  -0.0638   0.5109   1.0000
   2.250   0.7058   0.02966   0.01719  -0.0621   0.5055   1.0000
   2.500   0.7215   0.03033   0.01786  -0.0605   0.5006   1.0000
   2.750   0.7404   0.03080   0.01827  -0.0592   0.4968   1.0000
   3.000   0.7619   0.03115   0.01852  -0.0582   0.4937   1.0000
   3.250   0.7693   0.03233   0.01982  -0.0558   0.4882   1.0000
   3.500   0.7820   0.03316   0.02069  -0.0539   0.4836   1.0000
   3.750   0.7998   0.03369   0.02118  -0.0524   0.4800   1.0000
   4.000   0.8212   0.03406   0.02147  -0.0514   0.4772   1.0000
   4.250   0.8188   0.03574   0.02332  -0.0479   0.4716   1.0000
   4.500   0.8259   0.03684   0.02447  -0.0453   0.4670   1.0000
   4.750   0.8414   0.03746   0.02511  -0.0436   0.4635   1.0000
   5.000   0.8632   0.03780   0.02538  -0.0425   0.4608   1.0000
   5.250   0.8394   0.04047   0.02827  -0.0367   0.4544   1.0000
   5.500   0.8389   0.04187   0.02971  -0.0334   0.4499   1.0000
   5.750   0.8539   0.04246   0.03030  -0.0316   0.4466   1.0000
   6.000   0.8776   0.04269   0.03049  -0.0307   0.4442   1.0000
   6.250   0.7892   0.04834   0.03634  -0.0191   0.4343   1.0000
   6.500   0.7978   0.04918   0.03717  -0.0167   0.4309   1.0000
   6.750   0.8252   0.04919   0.03717  -0.0161   0.4286   1.0000
   7.250   0.7378   0.05782   0.04584  -0.0062   0.4130   1.0000
   7.500   0.6851   0.06483   0.05288  -0.0047   0.4012   1.0000
   7.750   0.7031   0.06558   0.05363  -0.0038   0.3981   1.0000
   8.000   0.7283   0.06570   0.05379  -0.0029   0.3960   1.0000
   8.250   0.6857   0.07221   0.06031  -0.0025   0.3847   1.0000
   8.500   0.7067   0.07282   0.06095  -0.0017   0.3817   1.0000
   9.000   0.6948   0.07931   0.06750  -0.0012   0.3684   1.0000
   9.250   0.7178   0.07977   0.06800  -0.0005   0.3655   1.0000
   9.500   0.6955   0.08479   0.07306  -0.0009   0.3568   1.0000
   9.750   0.7086   0.08629   0.07460  -0.0005   0.3522   1.0000
  10.000   0.7327   0.08670   0.07508   0.0001   0.3495   1.0000
  10.250   0.7093   0.09199   0.08042  -0.0006   0.3401   1.0000
  10.500   0.7257   0.09321   0.08170  -0.0003   0.3361   1.0000
  11.000   0.7263   0.09907   0.08767  -0.0008   0.3235   1.0000
  11.250   0.7458   0.10001   0.08867  -0.0004   0.3200   1.0000
  11.500   0.7344   0.10429   0.09304  -0.0013   0.3120   1.0000
  11.750   0.7461   0.10606   0.09488  -0.0013   0.3071   1.0000
  12.000   0.7692   0.10657   0.09546  -0.0008   0.3042   1.0000
  12.250   0.7503   0.11187   0.10083  -0.0023   0.2949   1.0000
  12.500   0.7691   0.11280   0.10184  -0.0020   0.2911   1.0000
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