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EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 544 AIRFOIL (e544-il)
Reynolds number: 200,000
Max Cl/Cd: 61.74 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e544-il-200000-n5.txt
Download as CSV file: xf-e544-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 544 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5013   0.09507   0.09127  -0.0614   1.0000   0.0076
 -13.500  -0.5232   0.08530   0.08140  -0.0673   1.0000   0.0075
 -13.250  -0.5473   0.07718   0.07315  -0.0719   1.0000   0.0074
 -13.000  -0.5760   0.06993   0.06572  -0.0749   1.0000   0.0074
 -12.750  -0.5949   0.06517   0.06082  -0.0760   1.0000   0.0073
 -12.500  -0.6200   0.06008   0.05554  -0.0761   1.0000   0.0074
 -12.250  -0.6372   0.05640   0.05169  -0.0754   1.0000   0.0073
 -12.000  -0.6567   0.05268   0.04777  -0.0738   1.0000   0.0073
 -11.750  -0.6728   0.04958   0.04447  -0.0717   1.0000   0.0073
 -11.500  -0.6861   0.04705   0.04177  -0.0690   1.0000   0.0073
 -10.750  -0.6732   0.03735   0.03103  -0.0691   0.9709   0.0075
 -10.500  -0.6537   0.03484   0.02816  -0.0699   0.9599   0.0077
 -10.250  -0.6281   0.03273   0.02581  -0.0715   0.9508   0.0079
 -10.000  -0.5976   0.03098   0.02390  -0.0740   0.9433   0.0082
  -9.750  -0.5662   0.02948   0.02225  -0.0763   0.9342   0.0085
  -9.500  -0.5315   0.02799   0.02059  -0.0789   0.9260   0.0090
  -9.250  -0.4977   0.02673   0.01914  -0.0812   0.9153   0.0098
  -9.000  -0.4653   0.02561   0.01791  -0.0836   0.9038   0.0108
  -8.750  -0.4343   0.02461   0.01680  -0.0855   0.8917   0.0118
  -8.500  -0.4064   0.02370   0.01571  -0.0866   0.8792   0.0130
  -8.250  -0.3862   0.02274   0.01470  -0.0866   0.8663   0.0137
  -8.000  -0.3675   0.02194   0.01380  -0.0861   0.8544   0.0147
  -7.750  -0.3504   0.02118   0.01290  -0.0851   0.8433   0.0163
  -7.500  -0.3350   0.02050   0.01216  -0.0839   0.8322   0.0183
  -7.250  -0.3202   0.01988   0.01149  -0.0824   0.8221   0.0214
  -7.000  -0.3060   0.01924   0.01078  -0.0808   0.8132   0.0262
  -6.750  -0.2943   0.01859   0.01012  -0.0788   0.8039   0.0332
  -6.500  -0.2828   0.01794   0.00946  -0.0767   0.7963   0.0453
  -6.250  -0.2746   0.01729   0.00889  -0.0741   0.7877   0.0642
  -6.000  -0.2699   0.01666   0.00836  -0.0709   0.7804   0.0928
  -5.750  -0.2661   0.01604   0.00791  -0.0674   0.7722   0.1315
  -5.250  -0.2651   0.01414   0.00672  -0.0597   0.7585   0.2905
  -5.000  -0.2709   0.01275   0.00606  -0.0549   0.7521   0.4424
  -4.750  -0.2531   0.01309   0.00710  -0.0519   0.7473   0.6002
  -4.500  -0.2297   0.01325   0.00714  -0.0511   0.7413   0.6304
  -4.250  -0.2032   0.01359   0.00733  -0.0506   0.7362   0.6478
  -4.000  -0.1761   0.01407   0.00768  -0.0500   0.7316   0.6634
  -3.750  -0.1497   0.01471   0.00827  -0.0491   0.7262   0.6782
  -3.500  -0.1212   0.01554   0.00904  -0.0482   0.7216   0.6913
  -3.250  -0.0907   0.01613   0.00954  -0.0479   0.7177   0.6966
  -3.000  -0.0642   0.01615   0.00948  -0.0477   0.7130   0.6991
  -2.750  -0.0389   0.01605   0.00928  -0.0475   0.7080   0.7018
  -2.500  -0.0135   0.01586   0.00896  -0.0475   0.7038   0.7050
  -2.250   0.0115   0.01555   0.00848  -0.0478   0.7002   0.7088
  -2.000   0.0377   0.01550   0.00838  -0.0477   0.6956   0.7099
  -1.750   0.0643   0.01545   0.00827  -0.0477   0.6913   0.7110
  -1.500   0.0916   0.01541   0.00815  -0.0478   0.6875   0.7123
  -1.250   0.1190   0.01535   0.00801  -0.0480   0.6840   0.7137
  -1.000   0.1449   0.01528   0.00790  -0.0480   0.6797   0.7150
  -0.750   0.1713   0.01522   0.00779  -0.0480   0.6757   0.7168
  -0.500   0.1984   0.01514   0.00764  -0.0483   0.6720   0.7186
   0.000   0.2521   0.01495   0.00734  -0.0488   0.6647   0.7220
   0.250   0.2787   0.01486   0.00720  -0.0491   0.6608   0.7241
   0.500   0.3059   0.01482   0.00712  -0.0493   0.6571   0.7254
   0.750   0.3339   0.01481   0.00708  -0.0496   0.6540   0.7263
   1.000   0.3605   0.01481   0.00709  -0.0497   0.6503   0.7272
   1.250   0.3866   0.01481   0.00711  -0.0497   0.6462   0.7282
   1.500   0.4136   0.01481   0.00711  -0.0498   0.6423   0.7293
   1.750   0.4414   0.01481   0.00709  -0.0501   0.6390   0.7304
   2.000   0.4685   0.01483   0.00711  -0.0503   0.6353   0.7317
   2.250   0.4940   0.01485   0.00717  -0.0502   0.6306   0.7333
   2.500   0.5207   0.01485   0.00718  -0.0503   0.6262   0.7349
   2.750   0.5490   0.01485   0.00715  -0.0507   0.6222   0.7364
   3.000   0.5745   0.01486   0.00720  -0.0506   0.6170   0.7378
   3.250   0.6006   0.01486   0.00722  -0.0507   0.6118   0.7393
   3.500   0.6285   0.01486   0.00721  -0.0511   0.6073   0.7407
   3.750   0.6540   0.01490   0.00730  -0.0509   0.6023   0.7416
   4.000   0.6786   0.01493   0.00741  -0.0505   0.5963   0.7426
   4.250   0.7055   0.01495   0.00745  -0.0506   0.5910   0.7437
   4.500   0.7295   0.01501   0.00759  -0.0501   0.5846   0.7450
   4.750   0.7542   0.01505   0.00769  -0.0497   0.5781   0.7465
   5.000   0.7800   0.01509   0.00778  -0.0496   0.5720   0.7480
   5.250   0.8031   0.01514   0.00792  -0.0490   0.5640   0.7495
   5.500   0.8284   0.01518   0.00797  -0.0488   0.5569   0.7510
   5.750   0.8509   0.01523   0.00812  -0.0481   0.5477   0.7526
   6.000   0.8744   0.01529   0.00823  -0.0475   0.5388   0.7542
   6.250   0.8972   0.01535   0.00832  -0.0469   0.5287   0.7558
   6.500   0.9179   0.01543   0.00850  -0.0458   0.5171   0.7572
   6.750   0.9378   0.01552   0.00866  -0.0446   0.5047   0.7584
   7.000   0.9562   0.01564   0.00883  -0.0430   0.4898   0.7599
   7.250   0.9729   0.01579   0.00903  -0.0412   0.4723   0.7616
   7.500   0.9872   0.01599   0.00922  -0.0389   0.4517   0.7635
   7.750   0.9973   0.01624   0.00945  -0.0359   0.4287   0.7656
   8.250   1.0103   0.01718   0.01021  -0.0291   0.3774   0.7698
   8.500   1.0148   0.01787   0.01081  -0.0257   0.3513   0.7719
   9.000   1.0208   0.01951   0.01232  -0.0190   0.3032   0.7756
   9.250   1.0227   0.02049   0.01324  -0.0158   0.2808   0.7777
   9.500   1.0256   0.02154   0.01424  -0.0131   0.2581   0.7799
   9.750   1.0280   0.02269   0.01534  -0.0105   0.2374   0.7823
  10.000   1.0307   0.02394   0.01655  -0.0081   0.2175   0.7851
  10.250   1.0345   0.02522   0.01778  -0.0061   0.1985   0.7878
  10.500   1.0376   0.02655   0.01910  -0.0041   0.1807   0.7902
  10.750   1.0408   0.02796   0.02049  -0.0023   0.1641   0.7925
  11.000   1.0446   0.02941   0.02193  -0.0006   0.1488   0.7951
  11.250   1.0484   0.03094   0.02344   0.0009   0.1340   0.7978
  11.500   1.0530   0.03248   0.02499   0.0021   0.1208   0.8007
  11.750   1.0578   0.03407   0.02658   0.0032   0.1085   0.8036
  12.000   1.0623   0.03569   0.02822   0.0044   0.0975   0.8062
  12.250   1.0667   0.03737   0.02993   0.0054   0.0878   0.8090
  12.500   1.0705   0.03918   0.03176   0.0063   0.0790   0.8122
  12.750   1.0761   0.04093   0.03356   0.0070   0.0706   0.8156
  13.000   1.0812   0.04281   0.03548   0.0075   0.0635   0.8194
  13.250   1.0842   0.04488   0.03759   0.0081   0.0569   0.8230
  13.500   1.0897   0.04679   0.03959   0.0086   0.0511   0.8272
  13.750   1.0931   0.04897   0.04182   0.0089   0.0460   0.8319
  14.000   1.0972   0.05115   0.04407   0.0091   0.0415   0.8366
  14.250   1.1001   0.05347   0.04648   0.0093   0.0380   0.8418
  14.500   1.1035   0.05581   0.04892   0.0094   0.0344   0.8476
  14.750   1.1050   0.05842   0.05162   0.0094   0.0318   0.8539
  15.000   1.1078   0.06091   0.05425   0.0093   0.0291   0.8617
  15.250   1.1080   0.06375   0.05719   0.0092   0.0270   0.8711
  15.500   1.1095   0.06648   0.06008   0.0090   0.0249   0.8844
  15.750   1.1108   0.06935   0.06313   0.0085   0.0229   0.9098
  16.250   1.1085   0.07584   0.06987   0.0067   0.0201   1.0000
  16.500   1.1085   0.07928   0.07341   0.0057   0.0188   1.0000
  16.750   1.1049   0.08330   0.07749   0.0043   0.0176   1.0000
  17.000   1.1040   0.08701   0.08133   0.0031   0.0164   1.0000
  17.250   1.1014   0.09103   0.08548   0.0016   0.0155   1.0000
  17.500   1.0982   0.09527   0.08980  -0.0002   0.0145   1.0000
  17.750   1.0920   0.10001   0.09464  -0.0021   0.0141   1.0000
  18.000   1.0885   0.10442   0.09920  -0.0040   0.0132   1.0000
  18.250   1.0845   0.10900   0.10391  -0.0061   0.0125   1.0000
  18.500   1.0794   0.11384   0.10887  -0.0085   0.0118   1.0000
  18.750   1.0732   0.11895   0.11407  -0.0111   0.0115   1.0000
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