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EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 344 AIRFOIL (e344-il)
Reynolds number: 50,000
Max Cl/Cd: 14.28 at α=-1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e344-il-50000.txt
Download as CSV file: xf-e344-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2820   0.11274   0.10681  -0.0308   1.0000   0.2001
  -9.000  -0.2547   0.10762   0.10173  -0.0285   1.0000   0.2111
  -8.750  -0.2818   0.10716   0.10148  -0.0299   1.0000   0.2174
  -8.500  -0.2594   0.10283   0.09723  -0.0277   1.0000   0.2314
  -8.250  -0.2616   0.10015   0.09471  -0.0269   1.0000   0.2402
  -8.000  -0.2814   0.09926   0.09406  -0.0259   1.0000   0.2512
  -7.750  -0.2726   0.09649   0.09148  -0.0232   1.0000   0.2655
  -7.500  -0.3101   0.09799   0.09331  -0.0170   1.0000   0.2642
  -7.250  -0.3454   0.09951   0.09505  -0.0130   0.9971   0.2618
  -7.000  -0.3129   0.09470   0.09025  -0.0193   0.9818   0.2933
  -6.750  -0.2774   0.09042   0.08596  -0.0236   0.9660   0.3346
  -6.500  -0.2393   0.08637   0.08191  -0.0261   0.9518   0.3882
  -6.250  -0.1994   0.08296   0.07850  -0.0266   0.9381   0.4598
  -6.000  -0.0792   0.07614   0.07156  -0.0277   0.9317   0.5906
  -5.750   0.0403   0.06894   0.06424  -0.0348   0.9225   0.7437
  -5.250   0.0769   0.06181   0.05696  -0.0460   0.8885   0.7087
  -5.000  -0.0227   0.06133   0.05660  -0.0458   0.8665   0.5817
  -4.750  -0.0886   0.05901   0.05438  -0.0462   0.8457   0.5157
  -4.500  -0.1418   0.05616   0.05141  -0.0498   0.8286   0.4492
  -4.250  -0.1459   0.05156   0.04525  -0.0634   0.8140   0.2475
  -4.000  -0.1102   0.04847   0.04087  -0.0645   0.8033   0.1632
  -3.750  -0.0925   0.04667   0.03864  -0.0625   0.7911   0.1442
  -3.500  -0.0563   0.04443   0.03563  -0.0624   0.7830   0.1297
  -3.250  -0.0435   0.04336   0.03438  -0.0602   0.7708   0.1272
  -3.000  -0.0214   0.04211   0.03278  -0.0589   0.7612   0.1256
  -2.750   0.0078   0.04070   0.03103  -0.0583   0.7521   0.1232
  -2.500   0.0275   0.04013   0.03016  -0.0568   0.7423   0.1216
  -2.250   0.3860   0.02892   0.02092  -0.0999   0.7324   1.0000
  -2.000   0.3992   0.02976   0.02145  -0.0985   0.7220   1.0000
  -1.750   0.4206   0.03008   0.02137  -0.0973   0.7146   1.0000
  -1.500   0.4304   0.03118   0.02232  -0.0957   0.7048   1.0000
  -1.250   0.4513   0.03160   0.02242  -0.0945   0.6981   1.0000
  -1.000   0.4586   0.03297   0.02371  -0.0928   0.6899   1.0000
  -0.750   0.4750   0.03371   0.02424  -0.0914   0.6830   1.0000
  -0.500   0.4852   0.03492   0.02533  -0.0896   0.6763   1.0000
  -0.250   0.4909   0.03639   0.02671  -0.0876   0.6692   1.0000
   0.000   0.5099   0.03712   0.02724  -0.0863   0.6642   1.0000
   0.250   0.5025   0.03944   0.02956  -0.0832   0.6581   1.0000
   0.500   0.4974   0.04150   0.03159  -0.0801   0.6522   1.0000
   0.750   0.5152   0.04237   0.03230  -0.0788   0.6474   1.0000
   1.000   0.5011   0.04500   0.03491  -0.0749   0.6432   1.0000
   1.250   0.4577   0.04875   0.03873  -0.0683   0.6404   1.0000
   1.500   0.4105   0.05199   0.04200  -0.0607   0.6393   1.0000
   1.750   0.3786   0.05456   0.04457  -0.0548   0.6392   1.0000
   2.000   0.3602   0.05689   0.04685  -0.0508   0.6409   1.0000
   2.250   0.3519   0.05901   0.04890  -0.0479   0.6428   1.0000
   2.500   0.3524   0.06101   0.05082  -0.0459   0.6446   1.0000
   2.750   0.1293   0.06587   0.05645  -0.0287   0.8269   1.0000
   3.000   0.1628   0.06886   0.05920  -0.0309   0.8181   1.0000
   3.250   0.1670   0.06924   0.05945  -0.0286   0.8038   1.0000
   3.500   0.1753   0.07032   0.06039  -0.0269   0.7914   1.0000
   3.750   0.2086   0.07350   0.06338  -0.0291   0.7838   1.0000
   4.000   0.2091   0.07372   0.06351  -0.0263   0.7699   1.0000
   4.250   0.2172   0.07497   0.06464  -0.0248   0.7584   1.0000
   4.500   0.2498   0.07806   0.06759  -0.0268   0.7496   1.0000
   4.750   0.2478   0.07833   0.06779  -0.0239   0.7368   1.0000
   5.000   0.2625   0.08036   0.06972  -0.0236   0.7285   1.0000
   5.250   0.2817   0.08223   0.07149  -0.0236   0.7168   1.0000
   5.500   0.2848   0.08326   0.07247  -0.0218   0.7050   1.0000
   5.750   0.3179   0.08673   0.07584  -0.0237   0.6978   1.0000
   6.000   0.3128   0.08692   0.07599  -0.0210   0.6854   1.0000
   6.250   0.3360   0.08993   0.07892  -0.0218   0.6787   1.0000
   6.500   0.3440   0.09100   0.07996  -0.0206   0.6658   1.0000
   6.750   0.3484   0.09253   0.08145  -0.0195   0.6568   1.0000
   7.000   0.3724   0.09519   0.08407  -0.0202   0.6477   1.0000
   7.250   0.3719   0.09629   0.08515  -0.0187   0.6372   1.0000
   7.500   0.4034   0.09986   0.08868  -0.0202   0.6294   1.0000
   7.750   0.3963   0.10033   0.08915  -0.0182   0.6183   1.0000
   8.000   0.4300   0.10440   0.09320  -0.0200   0.6119   1.0000
   8.250   0.4205   0.10456   0.09336  -0.0178   0.6001   1.0000
   8.500   0.4584   0.10939   0.09818  -0.0200   0.5943   1.0000
   8.750   0.4437   0.10893   0.09773  -0.0176   0.5825   1.0000
   9.000   0.4763   0.11355   0.10235  -0.0194   0.5770   1.0000
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