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EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 520 AIRFOIL (e520-il)
Reynolds number: 200,000
Max Cl/Cd: 47.73 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e520-il-200000.txt
Download as CSV file: xf-e520-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 520 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.6917   0.17452   0.17099   0.0238   1.0000   0.0316
 -16.500  -0.7837   0.13652   0.13307   0.0068   1.0000   0.0241
 -16.250  -0.8375   0.11792   0.11430  -0.0047   1.0000   0.0227
 -16.000  -0.8794   0.10406   0.10021  -0.0137   1.0000   0.0219
 -15.750  -0.9174   0.09245   0.08830  -0.0210   1.0000   0.0212
 -15.500  -0.9442   0.08388   0.07945  -0.0259   1.0000   0.0208
 -15.250  -0.9629   0.07729   0.07264  -0.0292   1.0000   0.0207
 -15.000  -0.9759   0.07207   0.06724  -0.0315   1.0000   0.0210
 -14.750  -0.9871   0.06739   0.06237  -0.0333   1.0000   0.0212
 -14.500  -0.9971   0.06307   0.05785  -0.0345   1.0000   0.0215
 -14.250  -1.0043   0.05925   0.05385  -0.0353   1.0000   0.0220
 -14.000  -1.0099   0.05571   0.05011  -0.0357   1.0000   0.0225
 -13.750  -1.0135   0.05249   0.04669  -0.0358   1.0000   0.0232
 -13.500  -1.0142   0.04961   0.04360  -0.0356   1.0000   0.0238
 -13.250  -1.0160   0.04715   0.04088  -0.0353   1.0000   0.0248
 -13.000  -1.0123   0.04400   0.03761  -0.0347   1.0000   0.0263
 -12.750  -1.0068   0.04207   0.03568  -0.0343   1.0000   0.0278
 -12.500  -1.0008   0.04023   0.03375  -0.0337   1.0000   0.0296
 -12.250  -0.9936   0.03839   0.03174  -0.0330   1.0000   0.0316
 -12.000  -0.9836   0.03624   0.02947  -0.0320   1.0000   0.0339
 -11.750  -0.9754   0.03459   0.02784  -0.0313   1.0000   0.0365
 -11.500  -0.9655   0.03315   0.02633  -0.0305   1.0000   0.0394
 -11.250  -0.9539   0.03187   0.02488  -0.0297   1.0000   0.0420
 -11.000  -0.9442   0.02999   0.02309  -0.0287   1.0000   0.0462
 -10.750  -0.9324   0.02877   0.02179  -0.0279   1.0000   0.0502
 -10.500  -0.9210   0.02731   0.02029  -0.0269   1.0000   0.0549
 -10.250  -0.9104   0.02602   0.01904  -0.0260   1.0000   0.0603
 -10.000  -0.8983   0.02474   0.01772  -0.0250   1.0000   0.0666
  -9.750  -0.8869   0.02355   0.01658  -0.0242   1.0000   0.0747
  -9.500  -0.8767   0.02231   0.01540  -0.0233   1.0000   0.0837
  -9.250  -0.8668   0.02130   0.01443  -0.0222   1.0000   0.0945
  -9.000  -0.8481   0.02024   0.01344  -0.0228   0.9785   0.1098
  -8.750  -0.8198   0.01921   0.01240  -0.0246   0.9617   0.1318
  -8.500  -0.7981   0.01824   0.01153  -0.0251   0.9479   0.1541
  -8.250  -0.7798   0.01750   0.01084  -0.0245   0.9367   0.1779
  -8.000  -0.7637   0.01689   0.01029  -0.0233   0.9269   0.2036
  -7.750  -0.7486   0.01631   0.00979  -0.0218   0.9184   0.2310
  -7.500  -0.7339   0.01577   0.00933  -0.0201   0.9109   0.2600
  -7.250  -0.7176   0.01525   0.00890  -0.0187   0.9043   0.2913
  -7.000  -0.7011   0.01476   0.00853  -0.0172   0.8983   0.3248
  -6.750  -0.6836   0.01433   0.00820  -0.0158   0.8930   0.3605
  -6.500  -0.6643   0.01393   0.00792  -0.0147   0.8873   0.3969
  -6.250  -0.6447   0.01359   0.00770  -0.0134   0.8827   0.4334
  -6.000  -0.6237   0.01333   0.00753  -0.0124   0.8785   0.4699
  -5.750  -0.6009   0.01315   0.00746  -0.0116   0.8735   0.5040
  -5.500  -0.5775   0.01308   0.00747  -0.0108   0.8692   0.5354
  -5.250  -0.5534   0.01313   0.00755  -0.0099   0.8658   0.5624
  -5.000  -0.5275   0.01324   0.00765  -0.0095   0.8614   0.5867
  -4.750  -0.5011   0.01344   0.00785  -0.0091   0.8570   0.6056
  -4.500  -0.4749   0.01368   0.00804  -0.0085   0.8534   0.6223
  -4.250  -0.4489   0.01396   0.00827  -0.0078   0.8500   0.6367
  -4.000  -0.4214   0.01424   0.00851  -0.0077   0.8454   0.6495
  -3.750  -0.3948   0.01450   0.00872  -0.0073   0.8412   0.6613
  -3.500  -0.3692   0.01472   0.00885  -0.0066   0.8375   0.6731
  -3.250  -0.3410   0.01508   0.00922  -0.0063   0.8336   0.6804
  -3.000  -0.3144   0.01528   0.00938  -0.0060   0.8287   0.6902
  -2.750  -0.2875   0.01554   0.00961  -0.0054   0.8246   0.6980
  -2.500  -0.2615   0.01572   0.00974  -0.0047   0.8212   0.7061
  -2.250  -0.2345   0.01595   0.00997  -0.0046   0.8159   0.7141
  -2.000  -0.2080   0.01610   0.01010  -0.0041   0.8113   0.7211
  -1.750  -0.1818   0.01625   0.01021  -0.0034   0.8075   0.7281
  -1.500  -0.1558   0.01637   0.01033  -0.0031   0.8024   0.7352
  -1.250  -0.1291   0.01652   0.01048  -0.0026   0.7972   0.7411
  -1.000  -0.1038   0.01652   0.01042  -0.0020   0.7931   0.7487
  -0.750  -0.0774   0.01668   0.01062  -0.0015   0.7877   0.7537
  -0.500  -0.0520   0.01667   0.01057  -0.0013   0.7820   0.7616
  -0.250  -0.0257   0.01669   0.01059  -0.0004   0.7779   0.7658
   0.000   0.0000   0.01678   0.01071   0.0000   0.7714   0.7714
   0.250   0.0257   0.01669   0.01059   0.0004   0.7658   0.7779
   0.500   0.0520   0.01667   0.01057   0.0012   0.7617   0.7820
   0.750   0.0775   0.01669   0.01063   0.0015   0.7538   0.7877
   1.000   0.1038   0.01653   0.01043   0.0020   0.7488   0.7931
   1.250   0.1292   0.01654   0.01050   0.0026   0.7413   0.7973
   1.500   0.1558   0.01638   0.01033   0.0031   0.7352   0.8024
   1.750   0.1818   0.01624   0.01020   0.0034   0.7279   0.8075
   2.000   0.2080   0.01608   0.01007   0.0041   0.7209   0.8113
   2.250   0.2344   0.01594   0.00996   0.0046   0.7138   0.8159
   2.500   0.2616   0.01572   0.00974   0.0047   0.7061   0.8212
   2.750   0.2875   0.01554   0.00962   0.0054   0.6982   0.8246
   3.000   0.3145   0.01529   0.00938   0.0060   0.6902   0.8287
   3.250   0.3411   0.01508   0.00922   0.0062   0.6804   0.8336
   3.500   0.3692   0.01472   0.00885   0.0066   0.6732   0.8375
   3.750   0.3948   0.01450   0.00872   0.0073   0.6614   0.8412
   4.000   0.4214   0.01424   0.00851   0.0077   0.6495   0.8454
   4.250   0.4489   0.01396   0.00827   0.0078   0.6368   0.8500
   4.500   0.4750   0.01368   0.00805   0.0085   0.6224   0.8534
   4.750   0.5012   0.01344   0.00785   0.0090   0.6056   0.8571
   5.000   0.5276   0.01324   0.00765   0.0095   0.5867   0.8614
   5.250   0.5536   0.01313   0.00755   0.0098   0.5625   0.8658
   5.500   0.5776   0.01308   0.00747   0.0107   0.5356   0.8692
   5.750   0.6010   0.01315   0.00747   0.0116   0.5041   0.8735
   6.000   0.6239   0.01334   0.00753   0.0123   0.4697   0.8785
   6.250   0.6449   0.01359   0.00770   0.0134   0.4333   0.8827
   6.500   0.6646   0.01393   0.00792   0.0146   0.3966   0.8872
   6.750   0.6839   0.01433   0.00821   0.0157   0.3601   0.8930
   7.000   0.7015   0.01476   0.00853   0.0171   0.3246   0.8982
   7.250   0.7179   0.01526   0.00891   0.0186   0.2910   0.9042
   7.500   0.7344   0.01578   0.00934   0.0200   0.2595   0.9109
   7.750   0.7491   0.01631   0.00979   0.0217   0.2308   0.9184
   8.000   0.7643   0.01690   0.01029   0.0232   0.2035   0.9269
   8.250   0.7805   0.01751   0.01085   0.0244   0.1779   0.9366
   8.500   0.7988   0.01824   0.01153   0.0250   0.1541   0.9478
   8.750   0.8205   0.01922   0.01240   0.0245   0.1316   0.9615
   9.000   0.8489   0.02024   0.01343   0.0226   0.1096   0.9783
   9.250   0.8676   0.02130   0.01443   0.0220   0.0943   1.0000
   9.500   0.8777   0.02232   0.01541   0.0231   0.0837   1.0000
   9.750   0.8881   0.02355   0.01657   0.0240   0.0745   1.0000
  10.000   0.8996   0.02474   0.01772   0.0248   0.0667   1.0000
  10.250   0.9116   0.02600   0.01902   0.0258   0.0602   1.0000
  10.500   0.9215   0.02737   0.02033   0.0267   0.0544   1.0000
  10.750   0.9336   0.02876   0.02179   0.0277   0.0500   1.0000
  11.000   0.9451   0.02997   0.02306   0.0284   0.0458   1.0000
  11.250   0.9549   0.03185   0.02486   0.0295   0.0419   1.0000
  11.500   0.9667   0.03317   0.02635   0.0303   0.0392   1.0000
  11.750   0.9760   0.03457   0.02781   0.0311   0.0362   1.0000
  12.000   0.9849   0.03643   0.02963   0.0319   0.0334   1.0000
  12.250   0.9945   0.03841   0.03177   0.0328   0.0313   1.0000
  12.500   1.0025   0.04026   0.03378   0.0335   0.0295   1.0000
  12.750   1.0081   0.04207   0.03568   0.0340   0.0277   1.0000
  13.000   1.0143   0.04405   0.03767   0.0345   0.0263   1.0000
  13.250   1.0174   0.04724   0.04097   0.0351   0.0247   1.0000
  13.500   1.0170   0.04964   0.04362   0.0354   0.0240   1.0000
  13.750   1.0151   0.05253   0.04673   0.0355   0.0232   1.0000
  14.000   1.0113   0.05579   0.05020   0.0354   0.0225   1.0000
  14.250   1.0057   0.05931   0.05391   0.0350   0.0219   1.0000
  14.500   0.9982   0.06321   0.05801   0.0342   0.0216   1.0000
  14.750   0.9885   0.06751   0.06250   0.0330   0.0213   1.0000
  15.000   0.9785   0.07195   0.06710   0.0313   0.0208   1.0000
  15.250   0.9638   0.07750   0.07286   0.0288   0.0208   1.0000
  15.500   0.9433   0.08441   0.08001   0.0254   0.0210   1.0000
  15.750   0.9237   0.09160   0.08741   0.0212   0.0209   1.0000
  16.000   0.8860   0.10307   0.09919   0.0141   0.0214   1.0000
  16.250   0.8370   0.11850   0.11489   0.0040   0.0227   1.0000
  16.500   0.7839   0.13697   0.13352  -0.0072   0.0242   1.0000
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