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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 50,000
Max Cl/Cd: 29.23 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e521-il-50000.txt
Download as CSV file: xf-e521-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 521 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7380   0.09183   0.08526  -0.0306   1.0000   0.1298
 -11.750  -0.7569   0.08485   0.07827  -0.0335   1.0000   0.1289
 -11.500  -0.7808   0.07831   0.07170  -0.0359   1.0000   0.1274
 -11.250  -0.8093   0.07242   0.06572  -0.0373   1.0000   0.1253
 -11.000  -0.8409   0.06728   0.06044  -0.0371   1.0000   0.1231
 -10.750  -0.8695   0.06314   0.05611  -0.0351   1.0000   0.1221
 -10.500  -0.8868   0.05947   0.05219  -0.0328   1.0000   0.1234
 -10.250  -0.9005   0.05593   0.04833  -0.0304   1.0000   0.1259
 -10.000  -0.9136   0.05244   0.04436  -0.0274   1.0000   0.1286
  -9.750  -0.9016   0.04936   0.04125  -0.0262   1.0000   0.1358
  -9.500  -0.9008   0.04614   0.03759  -0.0238   1.0000   0.1414
  -9.250  -0.8890   0.04370   0.03509  -0.0221   1.0000   0.1525
  -9.000  -0.8789   0.04122   0.03246  -0.0202   1.0000   0.1639
  -8.750  -0.8677   0.03900   0.03013  -0.0181   1.0000   0.1779
  -8.500  -0.8576   0.03718   0.02826  -0.0157   1.0000   0.1948
  -8.250  -0.8496   0.03539   0.02637  -0.0128   1.0000   0.2125
  -8.000  -0.8407   0.03395   0.02500  -0.0100   1.0000   0.2334
  -7.750  -0.8343   0.03257   0.02361  -0.0066   1.0000   0.2561
  -7.500  -0.8258   0.03137   0.02258  -0.0035   1.0000   0.2824
  -7.250  -0.8176   0.03020   0.02154  -0.0003   1.0000   0.3111
  -7.000  -0.8103   0.02912   0.02056   0.0031   1.0000   0.3433
  -6.750  -0.7998   0.02815   0.01982   0.0062   1.0000   0.3791
  -6.500  -0.7911   0.02725   0.01905   0.0096   1.0000   0.4182
  -6.250  -0.7786   0.02664   0.01871   0.0129   1.0000   0.4611
  -6.000  -0.7649   0.02635   0.01862   0.0165   1.0000   0.5062
  -5.750  -0.7468   0.02677   0.01925   0.0202   1.0000   0.5507
  -5.500  -0.7243   0.02799   0.02055   0.0240   1.0000   0.5908
  -5.250  -0.6980   0.02973   0.02225   0.0278   1.0000   0.6250
  -5.000  -0.6688   0.03164   0.02404   0.0313   1.0000   0.6551
  -4.750  -0.6411   0.03324   0.02544   0.0345   1.0000   0.6833
  -4.500  -0.6148   0.03446   0.02648   0.0373   1.0000   0.7107
  -4.250  -0.5903   0.03530   0.02714   0.0399   1.0000   0.7380
  -4.000  -0.5497   0.03635   0.02793   0.0402   1.0000   0.7639
  -3.750  -0.4934   0.03722   0.02853   0.0376   1.0000   0.7894
  -3.500  -0.4331   0.03751   0.02856   0.0332   1.0000   0.8155
  -3.250  -0.3888   0.03733   0.02815   0.0305   1.0000   0.8409
  -3.000  -0.3397   0.03702   0.02765   0.0266   1.0000   0.8653
  -2.750  -0.2837   0.03652   0.02694   0.0211   1.0000   0.8883
  -2.500  -0.2486   0.03598   0.02627   0.0186   1.0000   0.9112
  -2.250  -0.1897   0.03521   0.02534   0.0117   1.0000   0.9323
  -2.000  -0.1468   0.03456   0.02458   0.0070   1.0000   0.9531
  -1.750  -0.0898   0.03366   0.02357  -0.0005   1.0000   0.9720
  -1.500  -0.0324   0.03278   0.02261  -0.0084   1.0000   0.9907
  -1.250   0.0013   0.03223   0.02201  -0.0123   1.0000   1.0000
  -1.000   0.0006   0.03211   0.02188  -0.0098   1.0000   1.0000
  -0.750   0.0002   0.03202   0.02177  -0.0074   1.0000   1.0000
  -0.500   0.0000   0.03194   0.02169  -0.0049   1.0000   1.0000
  -0.250   0.0000   0.03190   0.02164  -0.0025   1.0000   1.0000
   0.000   0.0000   0.03189   0.02163   0.0000   1.0000   1.0000
   0.250   0.0000   0.03190   0.02164   0.0024   1.0000   1.0000
   0.500   0.0000   0.03194   0.02168   0.0049   1.0000   1.0000
   0.750  -0.0002   0.03201   0.02177   0.0074   1.0000   1.0000
   1.000  -0.0006   0.03210   0.02187   0.0098   1.0000   1.0000
   1.250  -0.0013   0.03222   0.02200   0.0123   1.0000   1.0000
   1.500   0.0326   0.03278   0.02260   0.0084   0.9906   1.0000
   1.750   0.0896   0.03365   0.02357   0.0005   0.9721   1.0000
   2.000   0.1468   0.03455   0.02457  -0.0070   0.9531   1.0000
   2.250   0.1901   0.03519   0.02534  -0.0117   0.9322   1.0000
   2.500   0.2482   0.03596   0.02625  -0.0185   0.9113   1.0000
   2.750   0.2838   0.03650   0.02692  -0.0212   0.8883   1.0000
   3.000   0.3399   0.03701   0.02763  -0.0267   0.8653   1.0000
   3.250   0.3896   0.03731   0.02814  -0.0306   0.8408   1.0000
   3.500   0.4335   0.03750   0.02854  -0.0333   0.8154   1.0000
   3.750   0.4934   0.03721   0.02853  -0.0376   0.7894   1.0000
   4.000   0.5498   0.03633   0.02792  -0.0402   0.7639   1.0000
   4.250   0.5903   0.03530   0.02714  -0.0399   0.7380   1.0000
   4.500   0.6144   0.03448   0.02649  -0.0373   0.7108   1.0000
   4.750   0.6410   0.03325   0.02545  -0.0345   0.6834   1.0000
   5.000   0.6688   0.03165   0.02405  -0.0313   0.6552   1.0000
   5.250   0.6981   0.02973   0.02225  -0.0279   0.6250   1.0000
   5.500   0.7244   0.02799   0.02056  -0.0241   0.5907   1.0000
   5.750   0.7471   0.02676   0.01924  -0.0202   0.5506   1.0000
   6.000   0.7651   0.02634   0.01861  -0.0165   0.5061   1.0000
   6.250   0.7788   0.02664   0.01870  -0.0130   0.4611   1.0000
   6.500   0.7914   0.02726   0.01905  -0.0096   0.4182   1.0000
   6.750   0.8000   0.02815   0.01982  -0.0062   0.3790   1.0000
   7.000   0.8104   0.02911   0.02055  -0.0031   0.3432   1.0000
   7.250   0.8178   0.03020   0.02153   0.0003   0.3111   1.0000
   7.500   0.8261   0.03138   0.02259   0.0035   0.2824   1.0000
   7.750   0.8344   0.03257   0.02361   0.0066   0.2560   1.0000
   8.000   0.8408   0.03394   0.02499   0.0099   0.2334   1.0000
   8.250   0.8496   0.03539   0.02637   0.0128   0.2124   1.0000
   8.500   0.8576   0.03718   0.02826   0.0157   0.1946   1.0000
   8.750   0.8677   0.03901   0.03013   0.0181   0.1779   1.0000
   9.000   0.8789   0.04121   0.03245   0.0202   0.1640   1.0000
   9.250   0.8889   0.04368   0.03507   0.0222   0.1524   1.0000
   9.500   0.9008   0.04613   0.03758   0.0238   0.1414   1.0000
   9.750   0.9015   0.04934   0.04123   0.0263   0.1359   1.0000
  10.000   0.9138   0.05241   0.04432   0.0274   0.1286   1.0000
  10.250   0.9005   0.05589   0.04828   0.0304   0.1258   1.0000
  10.500   0.8869   0.05941   0.05212   0.0329   0.1231   1.0000
  10.750   0.8697   0.06312   0.05609   0.0351   0.1220   1.0000
  11.000   0.8412   0.06724   0.06040   0.0371   0.1231   1.0000
  11.250   0.8094   0.07240   0.06571   0.0373   0.1253   1.0000
  11.500   0.7804   0.07833   0.07172   0.0358   0.1274   1.0000
  11.750   0.7567   0.08489   0.07832   0.0334   0.1289   1.0000
  12.000   0.7377   0.09189   0.08532   0.0305   0.1298   1.0000
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